Airworthiness Directives: Piper Aircraft Corporation PA24, PA30, and PA39 Series Airplanes

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93-CE-60-AD; Amendment 39-8951; AD 94-13-10]

Airworthiness Directives: Piper Aircraft Corporation PA24, PA30,

and PA39 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 74-13-

01, which currently requires inspecting (one-time) the stabilator

torque tube bearing support fittings for looseness on certain Piper

Aircraft Corporation (Piper) PA24, PA30, and PA39 series airplanes,

and, if looseness is found, incorporating Piper Part No. 760 835 (Hi-

Shear Rivet Replacement Kit). This action retains the initial

inspection of the stabilator torque tube bearing support fittings, and

makes these inspections repetitive unless the above referenced service

kit is incorporated. Incidents of looseness of the stabilator torque

tube bearing support fittings on several of the affected airplanes in

compliance with the current AD prompted this action. The actions

specified by this AD are intended to prevent loss of pitch control

because of looseness of the stabilator torque tube bearing support

fittings, which could result in loss of control of the airplane.

EFFECTIVE DATE: August 12, 1994.

ADDRESSES: Service information that applies to this AD may be obtained

from the Piper Aircraft Corporation, Customer Services, 2926 Piper

Drive, Vero Beach, Florida 32960. This information may also be examined

at the Federal Aviation Administration (FAA), Central Region, Office of

the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas

City, Missouri 64106; or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Christina Marsh, Aerospace Engineer,

FAA, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite

210C, Atlanta, Georgia 30349; telephone (404) 991-2910; facsimile (404)

991-3606.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to include an AD that would apply

to certain PA24, PA30, and PA39 series airplanes was published in the

Federal Register on Februrary 1, 1994 (59 FR 4605). The action proposed

to supsersede AD 74-13-01, Amendment 39-1870, with a new AD that would

retain the initial inspection of the stabilator torque tube bearing

support fittings, and make these inspections repetitive unless Piper

Part No. 760 835 (Hi-Shear Rivet Replacement Kit) is incorporated.

Interested persons have been afforded an opportunity to participate

in the making of this amendment. No comments were received on the

proposed rule or the FAA's determination of the cost to the public.

After careful review of all available information, the FAA has

determined that air safety and the public interest require the adoption

of the rule as proposed except for minor editorial corrections. The FAA

has determined that these minor corrections will not change the meaning

of the AD nor add any additional burden upon the public than was

already proposed.

The FAA estimates that 4,409 airplanes in the U.S. registry will be

affected by this AD, that it will take approximately 1 workhour per

airplane to accomplish the required action, and that the average labor

rate is approximately $55 an hour. Based on these figures, the total

cost impact of the AD on U.S. operators is estimated to be $242,495.

This figure does not account for any repetitive inspections that would

be required by this AD. However, incorporating Piper Part No. 760 835

(Hi-Shear Rivet Replacement Kit) on all four stabilator torque tube

bearing support fittings eliminates the need for the repetitive

inspection requirement of this AD. In addition, this kit may have been

incorporated through compliance with AD 75-27-08, Amendment 39-2624.

This AD requires inspecting the rivets of the stabilator torque tube

bearing support fittings, and incorporating the referenced kit if any

rivets are found misaligned. The cost figure presented above is based

on the assumption that none of the owners/operators affected by this AD

have incorporated Piper Part No. 760 835. The FAA anticipates that

numerous owners/operators have incorporated this kit, thereby reducing

the cost impact of the required action.

The regulations adopted herein will not have substantial direct

effects on the States, on the relationship between the national

government and the States, or on the distribution of power and

responsibilities among the various levels of government. Therefore, in

accordance with Executive Order 12612, it is determined that this final

rule does not have sufficient federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this action (1) is

not a ``significant regulatory action'' under Executive Order 12866;

(2) is not a ``significant rule'' under DOT Regulatory Policies and

Procedures (44 FR 11034, February 26, 1979); and (3) will not have a

significant economic impact, positive or negative, on a substantial

number of small entities under the criteria of the Regulatory

Flexibility Act. A copy of the final evaluation prepared for this

action is contained in the Rules Docket. A copy of it may be obtained

by contacting the Rules Docket at the location provided under the

caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

Accordingly, pursuant to the authority delegated to me by the

Administrator, the Federal Aviation Administration amends part 39 of

the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.

106(g); and 14 CFR 11.89.

Sec. 39.13 [Amended]

2. Section 39.13 is amended by removing AD 74-13-01, Amendment 39-

1870, and by adding a new airworthiness directive to read as follows:

94-13-10 Piper Aircraft Corporation: Amendment 39-8951; Docket No.

93-CE-60-AD; Supersedes AD 74-13-01, Amendment 39-1870.

Applicability: The following model and serial number airplanes,

certificated in any category, that have not incorporated Piper Part

No. 760 835 (Hi-Shear Rivet Replacement Kit) on all four stabilator

torque tube bearing support fittings:

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Models Serial Nos.

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PA24-180, PA24-250 and PA24-260......... 24-1 through 24-5047.

PA24-400................................ 26-2 through 26-148.

PA30.................................... 30-1 through 30-2000.

PA39.................................... 39-1 through 39-155.

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Note 1: Piper Part No. 760 835 (Hi-Shear Rivet Replacement Kit),

may have been incorporated through compliance with AD 75-27-08,

Amendment 39-2624. This AD requires inspecting the rivets of the

stabilator torque tube bearing support fittings, and incorporating

the referenced kit if any rivets are found misaligned. Airplanes

incorporating this kit on all four stabilator torque tube bearing

support fittings are not affected by this AD.

Compliance: Required within the next 100 hour time-in-service

(TIS) after the effective date of this AD, unless already

accomplished, and thereafter as indicated.

To prevent loss of pitch control because of looseness of the

stabilator torque tube bearing support fittings, which could result

in loss of control of the airplane, accomplish the following:

(a) Inspect the stabilator torque tube bearing support fittings

for looseness by accomplishing the following:

(1) Remove the tail cone and right rear aft fuselage access

door.

(2) Grasp the stabilator tip and shake the tip from left to

right and up and down.

Note 2: Piper Service Bulletin 411A, dated April 10, 1974,

specifies these same procedures for inspecting the stabilator torque

tube bearing support fittings.

(b) If looseness is found during the inspection specified in

paragraph (a) of this AD, prior to further flight, incorporate Piper

Part No. 760 835 (Hi-Shear Rivet Replacement Kit) on the affected

fitting, and reinstall the tail cone and right rear aft fuselage

access door.

(c) If looseness is not found during the inspection specified in

paragraph (a) of this AD, prior to further flight, reinstall the

tail cone and right rear aft fuselage access door, and reinspect the

stabilator torque tube bearing support fittings for looseness at

intervals not to exceed 100 hours TIS until Piper Part No. 760 835

(Hi-Shear Rivet Replacement Kit) is incorporated on all four

stabilator torque tube bearing support fittings.

(d) Incorporating Piper Part No. 760 835 (Hi-Shear Rivet

Replacement Kit) on all four stabilator torque tube bearing support

fittings is considered terminating action for the inspection

requirement of this AD.

(e) Special flight permits may be issued in accordance with

sections 21.197 and 21.199 of the Federal Aviation Regulations (14

CFR 21.197 and 21.199) to operate the airplane to a location where

the requirements of this AD can be accomplished.

(f) An alternative method of compliance or adjustment of the

compliance time that provides an equivalent level of safety may be

approved by the Manager, Atlanta Aircraft Certification Office

(ACO), 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The

request shall be forwarded through an appropriate FAA Maintenance

Inspector, who may add comments and then send it to the Manager,

Atlanta ACO.

Note 3: Information concerning the existence of approved

alternative methods of compliance with this AD, if any, may be

obtained from the Atlanta ACO.

(g) All persons affected by this directive may obtain copies of

the document referred to herein upon request to the Piper Aircraft

Corporation, 2926 Piper Drive, Vero Beach, Florida 32960; or may

examine this document at the FAA, Central Region, Office of the

Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City,

Missouri 64106.

(h) This amendment (39-8951) supersedes AD 74-13-01, Amendment

39-1870.

(i) This amendment (39-8951) becomes effective on August 12,

1994.

Issued in Kansas City, Missouri, on June 17, 1994.

Barry D. Clements,

Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 94-15380 Filed 6-24-94; 8:45 am]

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