STRUCTURAL REPAIR MANUAL

SEAT TRACKS

1. General

This topic contains repair procedures for Seat Tracks allocated in following
areas:
− From FR20 thru FR35 and FR47/51 thru FR67.
For STA (FR) designation, refer to Chapter 53−00−00 Page Block 001. The ap

propriate repairs are listed in Table 201 and are described in more detail
in the following text.

NOTE: Refer to each repair to determine the repair applicability.

NOTE: For the definition of repair categories, refer to Chapter 51−11−14.

NOTE: For Damage/Repair Data Recording, refer to Chapter 51−11−15.

2. Safety Precautions

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL
MANUFACTURERS INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
WARNING: OBEY THE MANUFACTURER’S INSTRUCTIONS WHEN YOU USE CLEANING AGENTS,
BONDING AND ADHESIVE COMPOUND, SEALANT, SPECIAL MATERIAL AND STRUC

TURE PAINT. THESE MATERIALS ARE DANGEROUS.

CAUTION: OBEY THE REPAIR EFFECTIVITY PER WEIGHT VARIANT AND AIRCRAFT TYPE
GIVEN IN THE RELEVANT PARAGRAPH.
CAUTION: FOR REPAIR EFFECTIVITY RELATED TO AIRCRAFT TYPE REFER TO PARAGRAPH
3, GIVEN IN THE INTRODUCTION OF THE SRM.

CAUTION: USE ONLY SPECIFIED CLEANING MATERIALS AND SOLUTIONS OR THEIR

EQUIVALENTS. THE SURFACE PROTECTION COULD BE DAMAGED IF UNSPECIFIED
MATERIALS ARE USED. IT IS IMPORTANT THAT THE MANUFACTURER’S MIX

ING, APPLICATION AND TREATMENT INSTRUCTIONS ARE FOLLOWED.

CAUTION: TO PREVENT DAMAGE TO THE SURFACE PROTECTION, MECHANICAL AND ELEC

TRICAL SYSTEMS, THE AREA SURROUNDING THE REPAIR MUST BE COVERED
WITH PLASTIC FOIL MASKING TAPE.

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3. Repair Scheme

REPAIR
REPAIR PROCEDURE PARAGRAPH FIGURE
CATEGORY
Seat Track − Cutout of Damaged
Portion Y−Stations ± 765 and ± 4.A. 201 A
1292
Seat Track − Splice Repair Y−Sta

tions ± 765 and ± 1292
This repair information is inac

tive. This repair information has 4.B. 202 A <1>
been moved to: INACTIVE INACTIVE INACTIVE
Chapter 53−11−15, Page Block 201
Chapter 53−21−15, Page Block 201
Chapter 53−41−15, Page Block 201
Partial Replacement of Seat Track
− Cutline between two Cross Beams 4.C. 203 A
Y−Stations ± 765 and ± 1292
Repair Scheme Table
Table 201
<1> This repair category is only applicable between FR20 thru FR35.
4. Seat Track − Repairs

CAUTION: OBEY THE REPAIR EFFECTIVITY PER WEIGHT VARIANT AND AIRCRAFT TYPE
GIVEN IN THE RELEVANT TABLE.

CAUTION: THIS REPAIR IS ONLY APPLICABLE BEFORE MODIFICATION 39700K12815.

FOR THE EFFECTIVITY OF THE GIVEN MODIFICATION, REFER TO THE MOD

IFICATION/SERVICE BULLETIN LIST GIVEN IN CHAPTER 53−20−00 PAGE
BLOCK 001 AND CHAPTER 53−40−00 PAGE BLOCK 001.

A. Seat Track − Cutout of Damaged Portion Y−Stations ± 765 and ± 1292

This repair is a cutout of a damaged portion of seat track with a mini

mum size of 76.2 mm (3.0 in) and is effective as follows:
− From FR20 thru FR35, Figure 201.

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 STRUCTURAL REPAIR MANUAL

AIRCRAFT WEIGHT VARIANT

000, 001, 002, 003, 004, 005,
A319−100
006, 007, 008, 009, 011, 012
A319−100CJ 002, 010
Effectivity per Weight Variant and Aircraft Type
Table 202
NOTE: Refer to Paragraph 23. ’Weight Variant Information’ in the
INTRODUCTION of the SRM. Tables in the subparagraphs give necessary
data about all weight variants and their required information for
allowable damage and repair applicability.
− From FR47/51 thru FR67, Figure 201.

AIRCRAFT WEIGHT VARIANT

A319−100 ALL
A319−100CJ ALL
Effectivity per Weight Variant and Aircraft Type
Table 203
NOTE: Refer to Paragraph 23. ’Weight Variant Information’ in the
INTRODUCTION of the SRM. Tables in the subparagraphs give necessary
data about all weight variants and their required information for
allowable damage and repair applicability.

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(1) Repair Materials

ITEM NOMENCLATURE QTY MATERIAL/REMARKS

1 Seat track section 1 Refer to Figure 201

2 L−profile 2 Refer to Figure 201
3 Nut plate AR Refer to Figure 201
− Sealant (Corrosion Inhibit
AR Material No. 09−013 (Refer to
ing Brush Consistency) Chapter 51−35−00)
− Cleaning Agent (Methyl− AR Material No. 11−003 (Refer to
Ethyl−Ketone) Chapter 51−35−00)
− Pretreatment for Painting AR Material No. 13−002 (Refer to
(Chemical Conversion Coat
Chapter 51−35−00)
ing, Yellow Aluminum)
− Storage Preservation (Tem
AR Material No. 15−005A (Refer to
porary Corrosion Preventive Chapter 51−35−00)
Compound)
− Structure Paint (Polyure
AR Material No. 16−001 (Refer to
thane Anti Corrosion Prim
Chapter 51−35−00)
er)
− Structure Paint (Polyure
AR Material No. 16−002 (Refer to
thane Top Coat, Grey) Chapter 51−35−00)
− Structure Paint (Wash AR Material No. 16−020 (Refer to
Primer) Chapter 51−35−00)
− Chromic Acid Anodizing AR (Refer to Chapter 51−21−11)
(CAA)
(2) Repair Instructions (Refer to Figure 201)

(a) Mark repair area (Refer to Figure 201).

(b) Cut out the damaged portion of seat track, chamfer the corners
and deburr the sharp edges of the cutout (Refer to Figure 201).
NOTE: The vertical cut must be pass through the center of a seat
mounting hole (Refer to Figure 201).

WARNING: CLEANING AGENT (MATERIAL NO. 11−003) IS DANGEROUS.

(c) Clean the edges of the cutout with cleaning agent (methyl−ethyl−
ketone) (Material No. 11−003).

WARNING: STRUCTURE PAINT (MATERIAL NO. 16−020) IS DANGEROUS.

WARNING: STRUCTURE PAINT (MATERIAL NO. 16−001) IS DANGEROUS.

(d) Treat the edges of the cutout with structure paint (wash primer)
(Material No. 16−020) and structure paint (polyurethane anti cor

rosion primer) (Material No. 16−001) (Refer to Chapter 51−23−00).

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(e) Manufacture the repair parts (Refer to Figure 201).

(f) Position the repair parts and drill all the fastener holes (Refer
to Figure 201).

NOTE: Use transition fit for Hi−Lok fastener installation (Refer

to Chapter 51−44−11).

(g) Countersink fastener holes (Refer to Figure 201).

NOTE: For countersinking of fastener holes, refer to Chapter
51−46−11.

(h) If there are floor panel attachment holes in the repair area,
temporarily attach the floor panels with several bolts and drill
through the holes to the repair parts.
(i) Remove the floor panels from the repair area.

(j) Remove the repair parts from the repair area.

(k) Drill and countersink holes for nut plate in L−Profile (Refer to
Figure 201).
NOTE: For countersinking of fastener holes, refer to Chapter
51−46−11.

NOTE: For hole dimension, refer to Chapter 51−44−11.

(l) Chamfer the corners, deburr the edges and all the holes of the
repair parts (Refer to Figure 201).
WARNING: CLEANING AGENT (MATERIAL NO. 11−003) IS DANGEROUS.

(m) Clean the repair parts using cleaning agent (methyl−ethyl−ketone)

(Material No. 11−003).

WARNING: CHROMIC ACID ANODIZING (CAA) IS DANGEROUS.

WARNING: PRETREATMENT FOR PAINTING (MATERIAL NO. 13−002) IS POI

SONOUS.

(n) Treat the repair parts with chromic acid anodizing (CAA) or pre

treatment for painting (chemical conversion coating, yellow alumi

num) (Material No. 13−002) (Refer to Chapter 51−21−11).
WARNING: STRUCTURE PAINT (MATERIAL NO. 16−001) IS DANGEROUS.

(o) Apply structure paint (polyurethane anti corrosion primer) (Mate

rial No. 16−001) to the repair parts (Refer to Chapter 51−23−00).

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WARNING: SEALANT (MATERIAL NO. 09−013) IS DANGEROUS.

(p) Apply sealant (corrosion inhibiting brush consistency) (Material

No. 09−013) to the mating surfaces of the repair parts (Refer to
Chapter 51−76−11).

WARNING: SEALANT (MATERIAL NO. 09−013) IS DANGEROUS.

(q) Place the repair parts in position and install fasteners wet with
sealant (corrosion inhibiting brush consistency) (Material No.
09−013) (Refer to Chapter 51−42−11 and 51−76−11).

NOTE: Make sure that the installation process is completed, or,

at least a fastener is set in every third hole, during the
curing time of the sealant (Refer to Chapter 51−42−11 and
51−76−00).
WARNING: CLEANING AGENT (MATERIAL NO. 11−003) IS DANGEROUS.

(r) Clean the repair area using cleaning agent (methyl−ethyl−ketone)

(Material No. 11−003).

WARNING: STRUCTURE PAINT (MATERIAL NO. 16−002) IS DANGEROUS.

(s) Apply structure paint (polyurethane top coat, grey) (Material No.
16−002) to the repair area (Refer to Chapter 51−23−00).

WARNING: DO NOT APPLY STORAGE PRESERVATION (MATERIAL NO. 15−005A) IN

AREA OF OXYGEN EQUIPMENT AND OXYGEN PIPES.

WARNING: STORAGE PRESERVATION (MATERIAL NO. 15−005A) IS DANGEROUS.

(t) Apply storage preservation (temporary corrosion preventive com

pound) (Material No. 15−005A) or equivalent to the repair area.

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Seat Track − Cutout of Damaged Portion

Figure 201

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B. Seat Track − Splice Repair

NOTE: This repair information is inactive. This repair information has

been moved to:
− Chapter 53−11−15 , Page Block 201
− Chapter 53−21−15 , Page Block 201
− Chapter 53−41−15 , Page Block 201

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STRUCTURAL REPAIR MANUAL

Seat Track − Splice Repair

Figure 202

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 STRUCTURAL REPAIR MANUAL

CAUTION: OBEY THE REPAIR EFFECTIVITY PER WEIGHT VARIANT AND AIRCRAFT TYPE
GIVEN IN THE RELEVANT TABLE.
CAUTION: THIS REPAIR IS APPLICABLE AFTER MODIFICATION 39700.

C. Partial Replacement of Seat Track − Cutline between two Crossbeams

NOTE: This repair is applicable to seat tracks at floor structure Sta

tions ± Y765 and ± Y1292 and is effective as follows:
− FR24 thru FR35

AIRCRAFT WEIGHT VARIANT

A319−100 ALL
A319−100CJ ALL
Effectivity per Weight Variant and Aircraft Type
Table 204
NOTE: Refer to Paragraph 23. ’Weight Variant Information’ in the
INTRODUCTION of the SRM. Tables in the subparagraphs give necessary
data about all weight variants and their required information for
allowable damage and repair applicability.

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 STRUCTURAL REPAIR MANUAL

(1) Repair Materials

ITEM NOMENCLATURE QTY MATERIAL/REMARKS

1 Seat Track 1 Refer to Figure 203

2 U−Profile 2 Refer to Figure 203
3 Strap 1 Refer to Figure 203
4 Shim 2 Refer to Figure 203
− Sealant (Corrosion inhibit
AR Material No. 09−013 (Refer to
ing brush consistency) Chapter 51−35−00)
− Cleaning agent (Methyl − AR Material No. 11−003 (Refer to
ethyl − ketone) Chapter 51−35−00)
− Pretreatment for painting AR Material No. 13−002 (Refer to
(Chemical conversion coat
Chapter 51−35−00)
ing, yellow aluminum)
− Storage preservation (Cor
AR Material No. 15−005A (Refer to
rosion preventive temporary Chapter 51−35−00)
protective compound)
− Structure paint (Anti Cor
AR Material No. 16−001 (Refer to
rosion primer) Chapter 51−35−00)
− Structure paint (Polyure
AR Material No. 16−002 (Refer to
thane top coat, grey) Chapter 51−35−00)
− Structure paint (Wash AR Material No. 16−020 (Refer to
primer) Chapter 51−35−00)
− Chromic Acid Anodizing AR Chapter 51−21−11
(CAA)
(2) Repair Instructions (Refer to Figure 203)

(a) Clean the damaged area with cleaning agent (Methyl−ethyl−ketone)

(Material No. 11−003).

(b) Examine the damage and calculate the repair area (Refer to Figure
203).

(c) Mark the repair area (Refer to Figure 203).

(d) Remove the existing fasteners in the repair area (Refer to Chap

ter 51−42−11).
(e) Cut out the damage in the seat track, deburr the edges of the
cutout and chamfer the corners (Refer to Figure 203).
NOTE: The cutline must be central in a seat mounting hole, with
at least one rivet pitch between the cutline and the near

est floor panel attachment hole (Refer to Figure 203).
(f) Clean the edges of the cutout with cleaning agent (Methyl−ethyl−
ketone) (Material No. 11−003).

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(g) Apply structure paint (Wash primer) (Material No. 16−020) to the
edges of the cutout (Refer to Chapter 51−23−00).
(h) Apply structure paint (Anti corrosion primer) (Material No.
16−001) to the edges of the cutout (Refer to Chapter 51−23−00).

(i) Prepare the repair parts (Refer to Figure 203).

(j) Position and clamp the repair parts (Refer to Figure 203).
(k) Drill all the fastener holes (Refer to Figure 203).

NOTE: For the fastener pitch and margin data (Refer to Chapter
51−47−00).

NOTE: Use transition fit for Hi−Lok fastener installation (Refer

to Chapter 51−44−11).
(l) If there are floor panel attachment holes in the repair area,
temporarily attach the floor panels with several bolts and drill
the attachment holes thru the repair parts.

NOTE: The use of drill bushes is recommended to avoid damage to

the attachment holes.
(m) Remove the floor panels from the repair area.

(n) Drill the floor panel attachment holes to the final dimension.

(o) Remove the repair parts and deburr the fastener holes and the
floor panels attachment holes.
(p) Chamfer the corners of the repair parts as necessary (Refer to
Figure 203).

(q) Clean the repair parts and the repair area with cleaning agent
(Methyl−ethyl−ketone) (Material No. 11−003).
(r) Apply structure paint (Wash primer) (Material No. 16−020) to the
new floor panel attachment holes in the seat tracks and longerons
(Refer to Chapter 51−23−00).

(s) Apply structure paint (Anti corrosion primer) (Material No.

16−001) to the new floor panel attachment holes in the seat
tracks and longerons (Refer to Chapter 51−23−00).

WARNING: CHROMIC ACID ANODIZING (CAA) IS DANGEROUS.

(t) Treat the repair parts with Chromic Acid Anodizing (CAA) or pre

treatment for painting (Chemical conversion coating, yellow alumi

num) (Material No. 13−002) (Refer to Chapter 51−21−11).
(u) Apply structure paint (Polyurethane primer) (Material No. 16−001)
to the repair parts (Refer to Chapter 51−23−00).

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(v) Apply sealant (Corrosion inhibiting brush consistency) (Material

No. 09−013) to the mating surfaces of the repair parts (Refer to
Chapter 51−76−11).

(w) Put the repair parts in position and install the fasteners wet
with sealant (Corrosion inhibiting brush consistency) (Material
No. 09−013) (Refer to Chapter 51−42−11 and Chapter 51−76−11).

NOTE: Make sure that the installation process is completed, or at

least a fastener is set in every third hole, during the
curing time of the sealant (Refer to Chapter 51−42−11 and
Chapter 51−76−11).

(x) Let the sealant (Corrosion inhibiting brush consistency) (Material

No. 09−013) cure.
NOTE: For the curing time of the sealant (Corrosion inhibiting
brush consistency) (Material No. 09−013), refer to the
manufacturer’s instructions.

(y) Clean the repair area with cleaning agent (Methyl−ethyl−ketone)

(Material No. 11−003).
(z) Apply structure paint (Polyurethane top coat, grey) (Material No.
16−002) to the repair area (Refer to Chapter 51−23−00).

WARNING: DO NOT APPLY CORROSION PREVENTIVE TEMPORARY PROTECTIVE COM

POUND (MATERIAL. 15−005A) IN AREA OF OXYGEN EQUIPMENT AND
OXYGEN PIPES.

(aa)Apply storage preservation (Corrosion preventive temporary protec

tive compound) (Material No. 15−005A) or equivalent to the repair
area (Refer to Chapter 51−23−00).

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Partial Replacement of Seat Track − Cutline between two Cross Beams Y−Sta

tions ± 765 and ± 1292
Figure 203

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