SERVICE 1156A NO.

Piper Aircraft, Inc.

2926 Piper Drive
BULLETIN
Vero Beach, FL, U.S.A. 32960
PIPER CONSIDERS
COMPLIANCE MANDATORY
Date: November 9, 2021 (S) (M)

Service Bulletin (SB) 1156A supersedes SB 1156 in its entirety. Aircraft that were previously made compliant
with SB 1156 are in compliance with SB 1156A until the next regularly scheduled event (inspection or replacement)
is due.

SUBJECT: PERIODIC INSPECTION AND REPLACEMENT OF

NOSE GEAR DRAG LINK BOLT

REASON FOR REVISION: SB 1156A adds the requirement to remove and inspect
the bolt at 100 hour intervals, regardless of the bolt’s total
time in service (TIS). Other changes update the document
to the current Piper format.

MODELS AFFECTED: SERIAL NUMBERS AFFECTED:

PA-28R-180 Arrow 28R-30002 through 28R-31270; 28R-7130001 through
28R-7130013
PA-28R-200 Arrow 28R-35001 through 28R-35820; 28R-7135001 through
28R-7135229
PA-28R-201 Arrow III 28R-7737002 through 28R-7837317; 2837001 through
2837061; 2844001 and Up
PA-28RT-201 Arrow IV 28R-7918001 through 28R-7918267; 28R-8018001
through 28R-8218026
PA-28RT-201T Turbo Arrow IV 28R-7918001 through 28R-7918267; 28R-8018001
through 28R-8218026
PA-44-180 Seminole 44-7995001 through 44-8195026; 4495001 through
4495013; 4496001 and Up
PA-44-180T Seminole 44-8107001 through 44-8207020

COMPLIANCE TIME: To coincide with the next regularly scheduled maintenance event, but not to
exceed the next 100 hours TIS, and on a recurring basis at an interval not to
exceed 100 hours TIS. In addition, subject bolts with a TIS of 500 hours or more
are to be replaced, regardless of condition.

APPROVAL: The engineering aspects of this service document have been shown to comply
with the applicable Federal Aviation Regulations and are FAA approved.

ATA/JASC: 3220

(OVER)
SERVICE BULLETIN NO. 1156A PAGE 2 of 4

PURPOSE: The bolt that fastens the upper and lower nose gear (NG) drag links can develop
wear in a manner that may not be detectable during routine maintenance and
inspection. Specifically, on some aircraft, score marks have been discovered
around the circumference of the bolt shank, midway along the length of the bolt.
By design, the bolt is free to rotate inside a set of bushings to allow relative
movement between the upper and lower drag links during landing gear extension
and retraction. Over an extended number of operating hours, this rotation can
generate the score marks described, causing stress concentrations to develop in
the bolt.
Left uncorrected, this condition could eventually result in bolt failure, with
subsequent nose gear collapse.
This service bulletin provides a schedule for the removal and inspection of this
bolt, (along with associated hardware) and the inspection of the mating bushings.
This service bulletin also mandates a replacement interval for this bolt, regardless
of condition.
The applicable Piper Airplane Maintenance Manuals (AMMs) or Service Manuals
(SMs) will be updated to include the contents of this service bulletin at their next
revision.

INSTRUCTIONS:

1. Jack the aircraft per the applicable Piper AMM or SM.

2. Disassemble the upper drag link from the lower drag link by removing the NAS464P4-27 bolt that functions as
a hinge pin for the two parts. See Figure 1 or Figure 2, as applicable.
Discard the cotter pin, regardless of condition. The castellated nut, washers and bushings may be reused,
depending on condition.
• If the TIS of the bolt is less than 500 hours: clean and inspect the bolt for damage (especially for score marks
around the circumference of the bolt shank, midway along the bolt’s length). If the bolt is serviceable, then
reinstall it; replace on condition.
• If the TIS of the bolt is 500 or more hours: replace it with a new NAS464P4-27 bolt, regardless of condition.
3. Before installing the bolt, inspect the bushings for excessive wear and verify the bushing inside diameters are
within the range of 0.2515 to 0.2495 inches. Replace bushings on condition.
4. Reassemble the upper and lower drag links per the applicable Piper AMM or SM. Take care to reposition
washers retained in Step 2. Reinstall the castellated nut retained in Step 2 and secure with a new MS24665-134
cotter pin.
5. Lubricate per the applicable Piper AMM or SM, as required.
6. Verify the proper operation of the nose gear, in accordance with the applicable Piper AMM or SM.
7. Remove airplane from jacks and return to service, per the applicable Piper AMM or SM.
8. Make a logbook entry documenting compliance with this service bulletin.
SERVICE BULLETIN NO. 1156A PAGE 3 of 4

Figure 1
Typical PA-28R/28RT Bolt Location

Figure 2
Typical PA-44 Bolt Location
SERVICE BULLETIN NO. 1156A PAGE 4 of 4

MATERIAL REQUIRED:
QUANTITY PIPER CODE NOMENCLATURE
1 (on condition) 402-940 BOLT (NAS464P4-27)
2 (on condition) 407-565 WASHER (AN960-416 or NAS1149F0463P)
1 (on condition) 404-393 NUT (AN320-4)
1 (required) 424-052 COTTER PIN (MS24665-134)
2 (on condition) 452-800 BEARING (87319-002)

AVAILABILITY OF PARTS: Your Piper Approved Service Center

EFFECTIVITY DATE: This service bulletin is effective upon receipt.

SUMMARY: Applicable factory participation is limited to new aircraft in warranty at the time of
compliance. Factory participation will remain in effect for a period of time not to
exceed 180 days from the date of this service bulletin.
Please contact your Piper Approved Service Center to make arrangements for
compliance with this service bulletin in accordance with the compliance time
indicated.

NOTE: Please notify the factory of any address/ownership corrections. Changes should include aircraft model,
serial number, and current owner’s name and address.

Corrections and/or changes should be directed to:

PIPER AIRCRAFT, INC.
Attn: Customer Service
2926 Piper Drive
Vero Beach, FL 32960
or:
CustomerService@piper.com
Please include in subject line: “Aircraft ownership update”