FAA Proposed AD Yoke Shaft Inspection On Certain Piper Aircraft

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FAA Proposed AD Yoke Shaft Inspection On Certain Piper Aircraft By Daniel Baxter

		November 1, 2009 - On Friday the FAA propose to adopt a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) PA-28, PA-32, PA-34 and PA-44 series airplanes. This proposed AD would require an inspection of the control wheel shaft for both the pilot and copilot sides and, if necessary, replacement of the control wheel shaft. This proposed AD results from two field reports of incorrectly assembled control wheel shafts. We are proposing this AD to detect and correct any incorrectly assembled control wheel shafts. This condition, if left uncorrected, could lead to separation of the control wheel shaft, resulting in loss of pitch and roll control. The FAA received two reports of control wheel shafts that have been incorrectly assembled at Piper. The first incident concerned the loss of the control wheel on a Piper Model PA-34-220T airplane, where the right-hand control wheel shaft and universal joint separated due to a misdrilled hole for the threaded taper pin.

The second report was of a ground inspection on a Piper PA-34-220T airplane that revealed a similar situation between the control wheel shaft and the universal joint in the left-hand side. Investigation following these reports revealed that the control wheel shafts had been incorrectly assembled at Piper and holes were misdrilled even though they may visually appear acceptable. The hole in the shaft may be too close to the end of the shaft, causing a significant reduction in joint strength. Since discovery of this problem, Piper has added a step to the manufacturing process and also introduced a fixture to ensure proper assembly of the control wheel shaft/universal joint. This condition, if not corrected, could result in separation of the control wheel shaft, resulting in loss of pitch and roll control. Piper Aircraft had put out a Service Bulletin No. 1197A, on September 1, 2009. The service information describes procedures for: Inspection on both the pilot and copilot control wheel columns; and If necessary, replacement of the control wheel shaft and the universal joint. The FAA are proposing this AD because they have evaluated all information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This proposed AD would require a mandatory inspection of the control wheel shaft for both the pilot and copilot sides. This proposed AD results from two field reports of incorrectly assembled control wheel shafts. The FAA is proposing this AD to detect and correct any incorrectly assembled control wheel shafts. This condition, if left uncorrected, could lead to separation of the control wheel shaft, resulting in loss of pitch and roll control.

The FAA estimate that this proposed AD would affect 41,928 airplanes in the U.S. registry at an proposed inspection cost of $1,677,120. Additionally any necessary replacements that would be required based on the results of the proposed inspection $1,430.

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.

The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, "General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

This AD applies to the following airplane models and serial numbers that are certificated in any category:


Models	Serial Nos.
PA–28–140	Serial Nos. 28–20001 through 28–26946 and 28–7125001 through 28–7725290.
PA–28–150	Serial Nos. 28–03; 28–1 through 28–4377; and 28–1760A.
PA–28–160	Serial Nos. 28–03; 28–1 through 28–4377; and 28–1760A.
PA–28–180	Serial Nos. 28–03; 28–671 through 28–5859; and 28–7105001 through 28–7205318.
PA–28S–160	Serial Nos. 28–1 through 28–1760 and 28–1760A.
PA–28S–180	Serial Nos. 28–671 through 28–5859 and 28–7105001 through 28–7105234.
PA–28–235	Serial Nos. 28–10001 through 28–11378; 28–7110001 through 28–7210023; 28E–11 and 28–7310001 through 28–7710089.
PA–28–236	Serial Nos. 28–7911001 through 28–8611008 and 2811001 through 2811050.
PA–28–151	Serial Nos. 28–7415001 through 28–7715314.
PA–28–161	Serial Nos. 2841001 through 2841365; 28–7716001 through 28–8216300; 28–8316001 through 28–8616057; 2816001 through 2816109; 2816110 through 2816119; and 2842001 through 2842305.
PA–28–180	Serial Nos. 28–E13 and 28–7305001 through 28–7505260.
PA–28–181	Serial Nos. 28–7690001 through 28–8690056; 28–8690061; 28–8690062; 2890001 through 2890205; 2890206 through 2890231; and 2843001 through 2843672.
PA–28–201T	Serial Nos. 28–7921001 through 28–7921095.
PA–28R–180	Serial Nos. 28R–30002 through 28R–31270 and 28R–7130001 through 28R–7130013.
PA–28R–200	Serial Nos. 28R–35001 through 28R–35820; 28R–7135001 through 28R–7135229; and 28R–7235001 through 28R–7635545.
PA–28R–201	Serial Nos. 28R–7737002 through 28R–7837317; 2837001 through 2837061; and 2844001 through 2844138.
PA–28R–201T	Serial Nos. 28R–7703001 through 28R–7803374 and 2803001 through 2803012.
PA–28RT–201	Serial Nos. 28R–7918001 through 28R–7918267 and 28R–8018001 through 28R–8218026.
PA–28RT–201T	Serial Nos. 28R–7931001 through 28R–8631005 and 2831001 through 2831038.
PA–32–260	Serial Nos. 32–03; 32–04; 32–1 through 32–1297; and 32–7100001 through 32–7800008.
PA–32–300	Serial Nos. 32–15; 32–21; 32–40000 through 32–40974; and 32–7140001 through 32–7940290.
PA–32S–300	Serial Nos. 32S–15; 32S–40000 through 32S–40974; and 32S–7140001 through 32S–7240137.
PA–32R–300	Serial Nos. 32R–7680001 through 32R–7880068.
PA–32RT–300	Serial Nos. 32R–7885002 through 32R–7985106.
PA–32RT–300T	Serial Nos. 32R–7787001 and 32R–7887002 through 32R–7987126.
PA–32R–301 (SP)	Serial Nos. 32R–8013001 through 32R–8613006; 3213001 through 3213028; and 3213030 through 3213041.
PA–32R–301 (HP)	Serial Nos. 3213029; 3213042 through 3213103; 3246001 through 3246217; 3246219; 3246223; 3246218; 3246220 through 3246222; and 3246224 through 3246244.
PA–32R–301T	Serial Nos. 32R–8029001 through 32R–8629008 and 3229001 through 3229003.
PA–32–301T	Serial Nos. 32–8024001 through 32–8424002.
PA–32–301	Serial Nos. 32–8006002 through 32–8606023; 3206001 through 3206019; 3206042 through 3206044; 3206047; 3206050 through 3206055; and 3206060.
PA–32R–301T	Serial Nos. 3257001 through 3257483.
PA–32–301FT	Serial Nos. 3232001 through 3232074.
PA–32–301XTC	Serial Nos. 3255001 through 3255014; 3255026, 3255015 through 3255025; 3255027; and 3255051.
PA–34–200	Serial Nos. 34–E4 and 34–7250001 through 34–7450220.
PA–34–200T	Serial Nos. 34–7570001 through 34–8170092.
PA–34–220T	Serial Nos. 34–8133001 through 34–8633031; 3433001 through 3433172; 3448001 through 3448037; 3448038 through 3448079; 3447001 through 3447029; and 3449001 through 3449377.
PA–44–180	Serial Nos. 44–7995001 through 44–8195026; 4495001 through 4495013; and 4496001 through 4496251.

Compliance

1)

Actions: Inspect the pilot and copilot control wheel columns for correct control wheel shaft installation.

Compliance: Within 100 hours time-in-service (TIS) after the effective date of this AD or within 60 days after the effective date of this AD, whichever occurs first.

Procedures: Follow Piper Aircraft, Inc. Mandatory Service Bulletin No. 1197A, dated September 1, 2009.

2)

Actions: If during the inspection required in paragraph (e)(1) of this AD an incorrectly installed control wheel shaft is found, replace the appropriate shaft with a new shaft.

Compliance: Before further flight after any inspection that finds incorrect installation of the control wheel shaft.

Procedures: Follow Piper Aircraft, Inc. Mandatory Service Bulletin No. 1197A, dated September 1, 2009.

3)

Actions: Inspect the universal joint when doing the action required in (e)(2) of this AD, and if any deterioration, excessive wear, or damage is found, replace the universal joint with a new universal joint.

Compliance: Before further flight after any inspection that finds incorrect installation of the control wheel shaft.

Procedures: Follow Piper Aircraft, Inc. Mandatory Service Bulletin No. 1197A, dated September 1, 2009.

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