IIL1946 Rev.

Installation Instructions and Limitations Document

Customer: Garuda
Operator: Garuda
Airframe: 777-300ER
Basic Seat Model No.: 980
Seat Model Name: Spectrum
TSO Seat Type: TSO-C127a Type A – Forward Facing
Underseat Baggage Allowance: 20 lb per passenger place
Dynamic Compliance Report(s): 19392 Revision A
Dynamic Test Plan(s): 19392 Revision A
Dynamic Test Report(s): 19393 Revision B
Static Compliance Report(s): 19394 Revision A
Component Maintenance Manual1: 25-22-56 Index #3573

The Installation Instructions and Limitations (IIL) contained in this document are applicable to the seat
assembly part numbers listed in Table 1. For other seat assemblies in this seat model family refer to IILs
applicable to those seats.

Note that the conditions and tests required for TSO approval of the subject articles are minimum
performance standards. It is the responsibility of those desiring to install the article(s) either on or within
a specific type or class of aircraft to determine that the aircraft installation conditions are within TSO
standards. The article(s) may be installed only if the installation is performed in accordance with 14 CFR
Part 43 or the applicable airworthiness requirements.

1
CMM provides information required to ensure continued airworthiness.

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B/E AEROSPACE, INC. • SEATING PRODUCTS GROUP • 1455 FAIRCHILD ROAD • WINSTON-SALEM, NC 27105
TEL: 336 767 2000 • FAX: 336 744 6934
 IIL1946 Rev. C

Table 1 Subject Seat Part Numbers

Part Number Description

1017014-001HF08 LH TRIPLE, 18.50” BACK
1017014-002HF08 RH TRIPLE, 18.50” BACK
1017014-003HF08 LH TRIPLE, 18.50” BACK, LAST ROW, NO VIDEO, NO FOOTRESTS, NO BMFT
1017014-004HF08 RH TRIPLE, 18.50” BACK, LAST ROW, NO VIDEO, NO FOOTRESTS, NO BMFT
1017014-005HF08 LH TRIPLE, 17.84” BACK
1017014-006HF08 RH TRIPLE, 17.84” BACK
1017014-007HF08 LH TRIPLE, 17.84” BACK, NO VIDEO, NO FOOTRESTS, NO BMFT
1017014-008HF08 RH TRIPLE, 17.84” BACK, NO VIDEO, NO FOOTRESTS, NO BMFT
1017014-009HF08 LH TRIPLE, 17.17” BACK, OFFSET (tar=19.72”)
1017014-010HF08 RH TRIPLE, 17.17” BACK, OFFSET (tar=19.72”)
1017014-011HF08 LH TRIPLE, 17.17” BACK, OFFSET (tar=19.22”)
1017014-012HF08 RH TRIPLE, 17.17” BACK, OFFSET (tar=19.22”)
1017014-013HF08 LH TRIPLE, 17.17” BACK, OFFSET (tar=17.72”), DELETHALIZED I/B CTR ARM, NO VIDEO & FOOTREST (I/B ONLY)
1017014-014HF08 RH TRIPLE, 17.17” BACK, OFFSET (tar=17.72”), DELETHALIZED I/B CTR ARM, NO VIDEO & FOOTREST (I/B ONLY)
1017014-015HF08 CTR TRIPLE, 18.50” BACK
1017014-017HF08 CTR TRIPLE, 18.50” BACK, EPL, LAST ROW, NO VIDEO, NO FOOTRESTS, NO BMFT
1017014-101HF08 LH F/R TRIPLE, 18.50” BACK

1017014-102HF08 RH F/R TRIPLE, 18.50” BACK

1017014-103HF08 CTR F/R TRIPLE, 18.50” BACK

1017016-001HF08 LH DOUBLE, 18.50” BACK, LAST ROW, NO VIDEO, NO FOOTRESTS, NO BMFT

1017016-002HF08 RH DOUBLE, 18.50” BACK, LAST ROW, NO VIDEO, NO FOOTRESTS, NO BMFT

Minimum Requirements for Installation

1. All subject seats must be installed using Boeing seat track P/N 151W6294-13 (B/E track P/N 49721021)
or seat tracks shown to be less critical with regard to seat fitting-to-track interface and seat track strength.
2. All seats must be installed as forward facing ONLY in passenger cabin compartment.
3. Seat weights must not exceed the maximum installed seat weights listed in Table 4.
4. Life vest stowage provision is approved to accept life vest P/N P01074-205W and P01074-221W,
manufactured by Eastern Aero Marine. Other approved life vests with equivalent final packed dimensions
and weight not exceeding 2.0 lb may be substituted without additional structural testing. Life vest
stowage compartment provides acceptable retention under static and dynamic load conditions.
5. Post-test seat deformations for each seat assembly are recorded in the referenced static and dynamic
test report(s) and support the installation limitations presented in Table 5. The seat installer is
responsible for applying the deformation data presented in the report to each seat and verifying that the
recorded deformations do not violate any egress requirements when a seat is installed in a given location
and at a given seat pitch in the cabin.
6. All seats may be installed at a yaw angle within ±2° of the qualified installation yaw angle listed in the
dynamic test report(s) listed above without additional testing provided all other regulatory requirements
are satisfied.
• Seats noted below in Table 2 must be installed at the angle shown, or less, relative to the aircraft
longitudinal axis.
7. If applicable, only seat part numbers shown in Table 3 may be installed in accordance with the front leg
and track adapter stud locations at the positions shown.
8. The seat installer is solely responsible for establishing compliance of the seat installation for the range of
occupants.

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 IIL1946 Rev. C

9. The seat installer must determine the requirements that are applicable for the aircraft in which the seat is
to be installed and install the seat in accordance with the most critical limitation.

Table 2 Certified Installation Angles

Certified
Seat P/N
0B Installation
Angle(s)
1017014-005HF08 4.26º CCW
1017014-006HF08 4.26º CW
1017014-009HF08 4.26º CCW
1017014-010HF08 4.26º CW
1017014-011HF08 4.26º CCW
1017014-012HF08 4.26º CW
1017014-013HF08 4.26º CCW
1017014-014HF08 4.26º CW
1017016-001HF08 4.26º CCW
1017016-002HF08 4.26º CW

Table 3 Track Break Seat Installation Locations

Track Adapter Front Stud Station Location(s)
9B

Allowable Forward Seat Station Allowable Aft Seat Station

Leg
Seat P/N Forward Aft
Location
1B

Adapter Aft Track Adapter Forward

Track Stud Track
Attachment Stud in Attachment Track Stud in
in Stud in
to Leg Adapter to Leg Adapter
Adapter Adapter
Inboard
N/A N/A N/A N/A N/A N/A
Leg
N/A
Outboard
N/A N/A N/A N/A N/A N/A
Leg

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 IIL1946 Rev. C

Table 4 Maximum Seat Weights

Lower
Maximum Upper
Life Vest Literature Misc. Maximum
Certified Literature Pocket
Seat P/N Weight (lb) Pocket Storage3 Installed Seat
Seat Contents (lb)
2B

(2 lb/vest) Contents (lb) (lb) Weight4 (lb)

Weight2 (lb) (3 lb/pax)
(3 lb/pax)
1017014-001HF08 149.5 6 N/A 9 N/A 164.5
1017014-002HF08 149.5 6 N/A 9 N/A 164.5
1017014-003HF08 149.5 6 N/A 9 N/A 164.5
1017014-004HF08 149.5 6 N/A 9 N/A 164.5
1017014-005HF08 149.5 6 N/A 9 N/A 164.5
1017014-006HF08 149.5 6 N/A 9 N/A 164.5
1017014-007HF08 149.5 6 N/A 9 N/A 164.5
1017014-008HF08 149.5 6 N/A 9 N/A 164.5
1017014-009HF08 149 6 N/A 9 N/A 164.0
1017014-010HF08 149 6 N/A 9 N/A 164.0
1017014-011HF08 149.5 6 N/A 9 N/A 164.5
1017014-012HF08 149.5 6 N/A 9 N/A 164.5
1017014-013HF08 149.5 6 N/A 9 N/A 164.5
1017014-014HF08 149.5 6 N/A 9 N/A 164.5
1017014-015HF08 150.3 6 N/A 9 N/A 165.3
1017014-017HF08 150.3 6 N/A 9 N/A 165.3
1017014-101HF08 211 6 N/A 9 N/A 226.0
1017014-102HF08 211 6 N/A 9 N/A 226.0
1017014-103HF08 209.9 6 N/A 9 N/A 224.9
1017016-001HF08 121 4 N/A 6 N/A 131.0
1017016-002HF08 121 4 N/A 6 N/A 131.0

2
The maximum certified seat weight is the maximum allowable weight for the seat with all items contained in the bill of materials installed
including occupant restraints, IFE, and dress covers. It does not include any equipment the seat installer may add to the seat, such as
emergency equipment or literature pocket contents. This weight may exceed production seat weight. This weight does not include 3%
allowance per AC25.562-1B, Appendix 3, Section 16.b(1).
3
The miscellaneous storage accounts for any additional storage provisioned such as magazines, water bottles, etc. except conventional
underseat baggage weight (if applicable).
4
The maximum installed seat weight is the maximum allowable weight for the seat with all components and includes all equipment the seat
installer may add to the seat, such as emergency equipment or literature pocket contents. This weight is equal to the minimum total tested
seat weight of all static/dynamic tests used for substantiation of the subject seat P/Ns. However, this weight must be verified against seat
track interface loads and other aircraft/structural limitations.

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 IIL1946 Rev. C

Table 5 Pitch / Setback Limitations for Installations to Satisfy Listed Qualification Criteria
Qualification Criteria
Seat-to Span of Minimum Front Acceptable
FAMILY

Seat Pitch5 Bulkhead HIC for Range of Femur Injury Criterion Installation
Seat P/N Minimum Row Setback
or from O/B Life Vest Occupants 5th Percentile for range of occupants
Egress8 to Meet All
4B

for Non- Front

Setback6 Cabin Wall Retrieval9 Female to 95 Percentile 5th percentile female to
th
Requirements7
(inches) Row HIC
3B

Male11 95th percentile male12

Aircraft10
1 Setback ≥ Seat Width or Zero 9.27” 11.5” 18.87” ≥ 34.03” (d) ≥ 24.03” (j) ≥ 34.03”
1017014-001HF08
(Sub 1017014-002HF08 Pitch N/A 28” 28” N/A 30”-34” (a) 30”-34” (h) 30”-34”
Group 1)
1 Setback ≥ Seat Width or Zero 9.27” 11.5” 18.87” ≥ 34.03” (d) ≥ 24.03” (j) ≥ 34.03”
1017014-003HF08
(Sub 1017014-004HF08 Pitch N/A 28” 28” N/A 30”-34” (a) 30”-34” (h) 30”-34”
Group 1)
1 Setback ≥ Seat Width or Zero 9.27” 11.5” 18.87” ≥ 34.03” (d) ≥ 24.03” (j) ≥ 34.03”
1017014-005HF08
(Sub 1017014-006HF08 Pitch N/A 28” 28” N/A 30”-34” (a) 30”-34” (h) 30”-34”
Group 1)
1 Setback ≥ Seat Width or Zero 9.27” 11.5” 18.87” ≥ 34.03” (d) ≥ 24.03” (j) ≥ 34.03”
1017014-007HF08
(Sub 1017014-008HF08 Pitch N/A 28” 28” N/A 30”-34” (a) 30”-34” (h) 30”-34”
Group 1)
1 Setback ≥ Seat Width or Zero 8.81” 11.5” 18.87” ≥ 34.03” (d) ≥ 24.03” (j) ≥ 34.03”
1017014-011HF08
(Sub 1017014-012HF08 Pitch N/A 28” 28” N/A 30”-34” (a) 30”-34” (h) 30”-34”
Group 2)
1 Setback ≥ Seat Width or Zero 8.81” 11.5” 18.87” ≥ 34.03” (d) ≥ 24.03” (j) ≥ 34.03”
1017014-013HF08
(Sub 1017014-014HF08
Group 2) Pitch N/A 28” 28” N/A 30”-34” (a) 30”-34” (h) 30”-34”

5
Seat-to-seat pitch is distance between centerline of front stud of itemized seat and centerline of front stud of seat immediately in front.
6
Setback is distance from centerline of front stud of front row seat to vertical plane through closest point of flat bulkhead. Seat installer should evaluate actual test results and/or head path
data and unique aircraft furnishings to ensure that 14 CFR 25.562(c)(5) is met, if applicable.
7
Specifies approved range, minimum, or maximum, as applicable, to meet all listed qualification criteria for the intended installation airframe referenced in this IIL.
8
Pitch / setback required to maintain minimum of 6” clearance after seat deformation per AC 25.562-1B, Appendix 2, Paragraph 2a.
9
Minimum seat pitch / setback for 5th to 95th percentile range of seated, belted occupants. Reference Test Data Sheet 04-26 Revision E.
10
The minimum front row setback determined by the strike zone defined in AC 25.17A Section 88.b(8) is 35" from the seat CRP to protect passenger from serious injury in an emergency landing
condition if the certification basis for installation for the specific airplane does not require meeting HIC or femur criteria of 14 CFR 25.562. 35” – CRP(16.38”) + Tolerance(0.25”)(see env dwg)
= 18.87”
11
Method used to obtain listed distance is identified after dimension as one of following:
a) HIC <1000, or
b) No head contact as demonstrated in referenced dynamic test report(s), or
c) Special condition for Boeing 777—Maximum head excursion for 50th-percentile male top of head, or
d) Graphically evaluated per criteria in AC25.562-1B, Paragraph 5(e) and Appendix 4, Paragraph 3.
Setback: 50” – SRP(16.22”) + Tolerance (0.25”) = 34.03”
Pitch: Upright(24.62”) + 50” – SRP(16.22”) + Tolerance (0.25”) = 58.65”, rounded to next whole number = 59”
12
Method used to obtain listed distance is identified after dimension as one of following:
h) Femur load <2250, or
i) No knee contact as demonstrated in referenced dynamic test report(s), or
j) Graphically evaluated per criteria in AC25.562-1B, Paragraph 12.i.
Setback: 40” – SRP(16.22”) + Tolerance (0.25) = 24.03”
Pitch: Upright(24.62”) + 40” – SRP(16.22”) + Tolerance (0.25) = 48.65”, rounded to next whole number = 49”
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 IIL1946 Rev. C

Qualification Criteria
Seat-to Span of Minimum Front Acceptable
FAMILY

Seat Pitch5 Bulkhead HIC for Range of Femur Injury Criterion Installation
Seat P/N Minimum Row Setback
or from O/B Life Vest Occupants 5th Percentile for range of occupants
Egress8 to Meet All
4B

for Non- Front

Setback6 Cabin Wall Retrieval9 Female to 95th Percentile 5th percentile female to Requirements7
(inches) Row HIC
3B

Male11 95th percentile male12

Aircraft10
1017014-009HF08 Setback ≥ Seat Width or Zero 9.18” 11.5” 18.87” ≥ 34.03 (d) ≥ 24.03” (j) ≥ 34.03”
2 1017014-010HF08 Pitch N/A 28” 28” N/A 30”-34” (a) 30”-34” (h) 30”-34”
1017016-001HF08 Setback ≥ Seat Width or Zero 9.18” 11.5” 18.87” ≥ 34.03 (d) ≥ 24.03” (j) ≥ 34.03”
2 1017016-002HF08 Pitch N/A 28” 28” N/A N/A13, 14 (a) N/A13, 14 (h) N/A13, 14
Setback ≥ Seat Width or Zero 8.85” 11.5” 18.87” ≥ 34.03” (d) ≥ 24.03” (j) ≥ 34.03”
3 1017014-015HF08
Pitch N/A 28” 28” N/A 30”-34” (a) 30”-34” (h) 30”-34”
Setback ≥ Seat Width or Zero 8.85” 11.5” 18.87” ≥ 34.03” (d) ≥ 24.03” (j) ≥ 34.03”
3 1017014-017HF08
Pitch N/A 28” 28” N/A 30”-34” (a) 30”-34” (h) 30”-34”
I/B & CTR PAX: I/B & CTR PAX: I/B & CTR PAX:
28.07” 15 15.92” 16 28.07” 15
1017014-101HF08 Setback ≥ Seat Width or Zero 15.89” 11.5” 18.87” (b) (b)
4 1017014-102HF08 O/B PAX: 21.3" O/B PAX: 10.42" O/B PAX: 21.3"
Pitch N/A 35” 28” N/A 30”-34” (a) 30”-34” (h) 30”-34”
Setback ≥ Seat Width or Zero 14.60” 11.5” 18.87” 26.74” 17
12F (b) ≥ 24.03” (j) ≥ 26.74”
5 1017014-103HF08
Pitch N/A 34” 28” N/A 30”-34” (a) 30”-34” (h) 30”-34”

13
Seat P/Ns 1017016-001HF08/002HF08 can only be installed behind any seat P/N at a pitch of 30-34" excluding seat P/N 1017014-013HF08 which can only be installed at a seat pitch of 31".
This also applies to the opposite seat hand P/N 1017016-002HF08 behind seat P/N 1017014-014HF08. See Figure 19 for more detail.
14
Seat P/Ns 1017016-001HF08/002HF08 are not qualified for HIC/Femur, therefore seats cannot be installed behind these seats.
15
See the Headpath Data Section and the Special Installation Instructions section.
16
See the Knee Path Data Section and the Special Installation Instructions section.
17
This value is based on the maximum top of head path excursion for a 50th percentile ATD.
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 IIL1946 Rev. C

Seat Deformation & Minimum Egress Analysis

The following table details the maximum deflections of the subject seats through all structural (static and dynamic)
testing. The figures illustrate the minimum setback and pitch for the respective family to maintain 6” egress.

Table 6 Subject Seat Deflection Table

Front Beam Front Corner of Maximum Maximum
Seat Deformation Armrest Deformation Deformation Deformation
Substantiated Seat Reference Above 25" Below 25"
Family
Part Number Figure
Number ΔX ΔY ΔZ ΔX ΔY ΔZ
ΔY (in.) ΔY (in.)
(in.) (in.) (in.) (in.) (in.) (in.)
1017014-001HF08
1017014-002HF08
1 1017014-003HF08
1017014-004HF08
Sub 1017014-005HF08
Figure 1 1.07 0.93 -0.06 1.50 1.15 -0.22 1.28 1.15
Group 1 1017014-006HF08
1017014-007HF08
1017014-008HF08
1 1017014-011HF08
1017014-012HF08
Sub 1017014-013HF08
Figure 2 0.63 0.54 -0.55 1.54 0.62 -0.77 0.60 0.62
Group 2 1017014-014HF08
1017014-009HF08
1017014-010HF08
2 1017016-001HF08
Figure 3 0.98 0.79 -0.61 1.85 1.04 -0.74 1.13 1.04
1017016-002HF08
1017014-015HF08
3 1017014-017HF08
Figure 4 0.65 0.32 -0.46 1.44 0.36 -0.56 0.37 0.47
4 1017014-103HF08 Figure 5 1.99 0.37 -2.04 2.61 0.50 -2.20 0.64 0.50
1017014-101HF08
5 1017014-102HF08
Figure 6 0.82 0.56 0.44 1.23 0.77 0.01 0.98 0.73

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 IIL1946 Rev. C

Figure 1 Minimum Pitch/Setback Maintaining 6” Egress- Family 1 Sub Group 1

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 IIL1946 Rev. C

Figure 2 Minimum Pitch/Setback Maintaining 6” Egress- Family 1 Sub Group 2

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 IIL1946 Rev. C

Figure 3 Minimum Pitch/Setback Maintaining 6” Egress- Family 2

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 IIL1946 Rev. C

Figure 4 Minimum Pitch/Setback Maintaining 6” Egress- Family 3

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 IIL1946 Rev. C

Figure 5 Minimum Pitch/Setback Maintaining 6” Egress- Family 4

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 IIL1946 Rev. C

Figure 6 Minimum Pitch/Setback Maintaining 6” Egress- Family 5

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 IIL1946 Rev. C

Head Path Data:

Front Row Seat P/N 1017014-101HF08
Test WS5219, per DTR19393, established the front row head path for seat part number 1017014-101HF08 per
ARP5482. Knee path data for this seat is shown in the Knee Path Section.
th
The data below illustrates the path of the top of the head on the respective 50 percentile ATD. The values are
referenced from the front stud and the top of track. Two head path analyses were done for the I/B ATD and one
for the O/B ATD. The I/B ATD is used to substantiate the Center ATD since the headpath is larger on the I/B ATD.

TOP OF HEAD
MAX: 28.07 in

HEAD CG
MAX: 23.28 in

TH
Figure 7 I/B 50 Percentile ATD Head CG and Top of Head Path, O/B Seat (WS 5219)

TOP OF HEAD
MAX: 21.30 in

HEAD CG
MAX: 16.61 in

TH
Figure 8 O/B 50 Percentile ATD Head CG and Top of Head Path, O/B Seat (WS5219)

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 IIL1946 Rev. C

TH
Figure 9 I/B 50 Percentile ATD Head CG, O/B Seat (WS5219)

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 IIL1946 Rev. C

TH
Figure 10 O/B 50 Percentile ATD Head CG, O/B Seat (WS5219)

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 IIL1946 Rev. C
Front Row Seat P/N 1017014-103HF08
Test WS5214, per DTR1933, established the front row head path for seat part number 1017014-103HF08 per
ARP5482. The head path data is more critical than the knee path data and is therefore used for installation
th
limitations. The data below illustrates the path of the top of the head for the respective 50 percentile ATD. The
values are referenced from the front stud and the top of track.

TH
Figure 11 Right 50 Percentile ATD Head CG and Top of Head Path, CTR Seat (WS5214)

TH
Figure 12 Center 50 Percentile ATD Head CG and Top of Head Path, CTR Seat (WS5214)

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 IIL1946 Rev. C

TH
Figure 13 Right 50 Percentile ATD Head CG, O/B Seat (WS5214)

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 IIL1946 Rev. C

18 TH
Figure 14 Center 50 Percentile ATD Head CG, O/B Seat (WS5214)

18
The first row in this figure says "Left ATD" but is referring to the center PAX. There was double occupancy (Center and Right) during the test
and the center ATD was labeled as the left ATD.

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 IIL1946 Rev. C

Knee Path Data:

Front Row Seat P/N 1017014-101HF08
Test WS5219, per DTR19393, established the front row knee path for seat part number 1017014-101HF08 per
ARP5482.
th
The data below illustrates the path of the knee pivot on the respective 50 percentile ATD. The values are
referenced from the front stud and the top of track. Two knee path analyses were done for the I/B ATD and one
for the O/B ATD. The I/B ATD is used to substantiate the Center ATD since the knee path is larger on the I/B
ATD.

For the I/B pax the knee path data was measured at the knee pivot, an additional 2.4" needs to be added to get
the location of the front of the knee. This measurement is calculated from Appendix J on page J32 as "Knee
Front" - "Knee Pivot" (37.2" - 34.8" = 2.4"). Per Figure 15 the maximum knee pivot excursion is 13.52" which
would give a maximum front of knee excursion of 15.92"

TH
Figure 15 I/B 50 Percentile ATD Head CG and Knee Pivot Path, O/B Seat (WS 5219)

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 IIL1946 Rev. C

TH
Figure 16 I/B 50 Percentile ATD Knee Pivot, O/B Seat (WS5219)

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 IIL1946 Rev. C
For the O/B pax the knee path data was measured at the knee pivot, an additional 2.4" needs to be added to get
the location of the front of the knee. This measurement is calculated from Appendix J on page J37 as "Knee
Front" - "Knee Pivot" (36.9" - 34.5" = 2.4"). Per Figure 15 the maximum knee pivot excursion is 8.02" which would
give a maximum front of knee excursion of 10.42"

TH
Figure 17 O/B 50 Percentile ATD Head CG and Knee Pivot Path, O/B Seat (WS 5219)

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 IIL1946 Rev. C

TH
Figure 18 O/B 50 Percentile ATD Knee Pivot, O/B Seat (WS5219)

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 IIL1946 Rev. C

Special Installation Limitations

Seat P/N 1017016-001HF08/002HF08

Double seat P/N 1017016-001HF08 can be installed behind any seat P/N at a pitch of 30-34" except when
installed behind seat P/N 1017014-013HF08. Then seat P/N 1017016-001HF08 must be installed behind triple
seat P/N 1017014-013HF08 in the configuration shown in Figure 19 below at a 31” seat pitch. The seats must
also be installed in the aft portion of the aircraft canted at 4.26º. This also applies to the opposite seat hand P/N
1017016-002HF08 behind seat P/N 1017014-014HF08. Seat P/Ns 1017016-001HF08/002HF08 are not qualified
for HIC/Femur, therefore seats cannot be installed behind these seats.

Seat P/N
1017016-001HF08

Seat P/N
1017014-013HF08

Figure 19 Special Installation for Seat P/N 1017016-001HF08 behind Seat P/N 1017014-013HF08

Seat P/N 1017014-101HF08/102HF08

Front row seat P/Ns 1017014-101HF08/102HF08 have two head/knee paths, one for the O/B pax and one for the
I/B and CTR pax. The I/B & CTR pax have a maximum top of head excursion of 28.07" and maximum knee
excursion of 15.92" while the O/B pax has a head excursion of 21.3" and a maximum knee excursion of 10.42".
The installer must take this into consideration when approving the seat installation particularly when installing the
seat behind a door bustle.

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 IIL1946 Rev. C

Installation Instructions

WARNING: DO NOT USE EXCESSIVE FORCE ON TRACK LOCK AS IT

MAY CAUSE BURRING OR WRENCHING. REMOVE ALL SHARP EDGES.

(1) Verify seat installation location using installation drawing. Pay particular attention to seats spanning
track breaks at transition from constant section to non-constant section of aircraft, if applicable.
(2) Place track studs and track fittings at base of each leg assembly into corresponding openings in
aircraft seat tracks. Ensure that seat is not racked with respect to aircraft seat tracks.
(3) Slide seat assembly forward or aft approximately one half inch until locking mechanism on track fitting
can be pressed into seat track opening.
(4) To lock track fitting into position, use torque wrench to tighten Allen setscrew on top of fitting. This
will push shear plunger against top surface of aircraft seat tracks. Be certain to apply torque specified
on installation drawing to complete seat installation.
(5) Tighten anti-rattle nut or track adapter floor attachment bolts under forward portion of each leg to
torque specified on installation drawing. If no torque is specified, lift seat between track lip and front
stud to ensure no gap and shaking; tighten anti-rattle device by hand and then tighten additional ¼-
turn using anti-rattle nut wrench until secure in seat track.
(6) Verify seat is installed in correct location per installation drawing.
(7) If seat is equipped with in-seat electrical cabling, connect in-seat electrical cabling to aircraft seat-to-
seat cables in accordance with aircraft electrical installation drawing.

Data That May Be Used by the Installer in Approving an Installation

The following data has been included in the TSO data package and may be used by the installer for the purpose
of installation approval.

• The seat part numbers listed in Table 7 below have been evaluated for installation adjacent to Type III
Exits in the airframe listed in this IIL. The seat installer is responsible for using the test data provided in
the referenced test report(s) to evaluate egress requirements for the seat-to-seat pitch listed below.

Table 7 Type III Exit Seat(s)

Seat P/N
5B

N/A
N/A

• The seat assemblies contain integrated electronic equipment that is covered under the seat TSO
authorization per option 7b of AC21-49. The TSO approval of the subject seat assemblies cover the
attributes of the integrated electronic components for the attributes listed in Table 1 of AC21-49. The TC
or STC applicant for the seat system installation on the aircraft is responsible for all other regulatory
requirements associated with the integrated electronic components.

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 IIL1946 Rev. C

Additional Requirements for Continued Airworthiness,

Reconfiguration, and Spare Parts
• Continued TSO compliance of these seats can be ensured only through the exclusive use of replacement
parts approved by B/E Aerospace Seating Products Group per the referenced CMM or an applicable
service document approved by the TSO holder (B/E Aerospace SPG). Modifications to the seats
without the express written approval of the TSO holder (B/E Aerospace SPG) may void the TSO
certification. This includes any physical modifications to cushions or dress covers.
• Persons other than the TSO holder can make modifications to the TSO article in accordance with 14 CFR
21.619(c) and Advisory Circular (AC) 21-25A. Changes to seat restraint systems and cushion/dress
cover assemblies require additional coordination with the seat TSO holder.
• Note the following information with respect to the occupant restraint system:
o Only the occupant restraints identified in the CMM may be installed. Some seats in this
configuration may have different restraints installed on individual passenger places.
Exercise caution when replacing restraints to ensure proper installation.

Table 8 Occupant Restraints Installed on Subject Seats

Seat Part Number Seat Belt Part Number

6B Seat Belt Type
7B Manufacturer
8B

1017014-001HF08
1017014-002HF08
1017014-003HF08
1017014-004HF08
1017014-005HF08
1017014-006HF08
1017014-007HF08
1017014-008HF08
1017014-009HF08
All PAX
1017014-010HF08 Lap Belt
2011-1-519-2845
1017014-011HF08
1017014-012HF08
1017014-013HF08
1017014-014HF08
1017014-015HF08 AmSafe
1017014-017HF08
1017016-001HF08
1017016-002HF08
1017014-103HF08
Lap Belt
I/B & CTR PAX
2011-1-519-2845
1017014-101HF08 2011-1-519-2845
O/B PAX
Y-Belt
2124-1-063-8028
2124-1-063-8028
Lap Belt
I/B & CTR PAX
2011-1-519-2845
2011-1-519-2845
1017014-102HF08
O/B PAX
Y-Belt
2124-1-053-8028(RH)
2124-1-053-8028

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