28732 Federal Register / Vol. 61, No. 110 / Thursday, June 6, 1996 / Rules and Regulations

known as Pitts Models S–1S, S–1T, S–2, S–

2A, S–2S, and S–2B airplanes), all serial

numbers, certificated in any category, that are

equipped with aft lower fuselage wing attach

fittings incorporating part number (P/N)

76090, 2–2107–1, or 1–210–102, and where

these aft lower fuselage wing attach fittings

on both wings have not been modified in

accordance with the ACCOMPLISHMENT

INSTRUCTIONS section of Aviat Service

Bulletin (SB) No. 25, dated April 3, 1996.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (e) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required initially within the

next 50 hours time-in-service (TIS) after the

effective date of this AD, unless already

accomplished, and thereafter at intervals not

to exceed 50 hours TIS.

To prevent possible in-flight separation of

the wing from the airplane caused by a

cracked aft lower fuselage wing attach fitting,

accomplish the following:

(a) Inspect the aft lower fuselage wing

attach fitting on both wings for cracks in

accordance with the ACCOMPLISHMENT

INSTRUCTIONS section of Aviat Service

Bulletin (SB) No. 25, dated April 3, 1996.

(b) If any cracked aft lower fuselage wing

attach fitting is found during any inspection

required by this AD, prior to further flight,

modify the cracked aft lower fuselage wing

attach fitting in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section of Aviat SB No. 25, dated April 3,

1996. Repetitive inspections are no longer

necessary on a cracked aft lower fuselage

wing attachment fitting that has the

referenced modification incorporated.

(c) Modifying the aft lower fuselage wing

attach fitting on both wings in accordance

with the ACCOMPLISHMENT

INSTRUCTIONS section of Aviat SB No. 25,

dated April 3, 1996, is considered

terminating action for the repetitive

inspection requirement of this AD.

(d) 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.

(e) An alternative method of compliance or

adjustment of the initial or repetitive

compliance times that provides an equivalent

level of safety may be approved by the

Manager, Denver Aircraft Certification Office,

5440 Roslyn Street, suite 133, Denver,

Colorado 80216. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Denver ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Denver ACO.

(f) The inspection and modification (if

necessary) required by this AD shall be done

in accordance with Aviat Service Bulletin

No. 25, dated April 3, 1996. This

incorporation by reference was approved by

the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51. Copies may be obtained from Aviat

Aircraft, Inc., P.O. Box 1240 (postal service

delivery), 672 South Washington Street

(express mail), Afton, Wyoming 83110.

Copies may be inspected at the FAA, Central

Region, Office of the Assistant Chief Counsel,

Room 1558, 601 E. 12th Street, Kansas City,

Missouri, or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(g) This amendment (39–9645) becomes

effective on June 24, 1996.

Issued in Kansas City, Missouri, on May

29, 1996.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 96–14051 Filed 6–5–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 90–CE–60–AD; Amendment 39–

9654; AD 96–12–12]

RIN 2120–AA64

Airworthiness Directives; The New

Piper Aircraft, Inc. (formerly Piper

Aircraft Corporation) Models PA31,

PA31–300, PA31–325, and PA31–350

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule

SUMMARY: This amendment supersedes

Airworthiness Directive (AD) 80–22–04,

which currently requires the following

on The New Piper Aircraft, Inc. (Piper)

Models PA31, PA31–300, PA31–325,

and PA31–350 airplanes: repetitively

inspecting the upper section of Fuselage

Station (FS) 317.75 bulkhead for cracks,

and incorporating a certain

reinforcement kit if any crack is found.

This action requires inspecting (onetime) the upper section of the FS 317.75

bulkhead for cracks, and incorporating

one of two reinforcement kits depending

on whether cracks are found in the FS

317.75 bulkhead area. Cracks found on

airplanes in compliance with the

inspection requirements of AD 80–22–

04 and the Federal Aviation

Administration’s policy on aging

commuter-class aircraft prompted this

action. The actions specified in this AD

are intended to prevent structural

failure of the vertical fin forward spar

caused by cracks in the FS 317.75

bulkhead, which, if not detected and

corrected, could result in loss of control

of the airplane.

DATES: Effective July 16, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 16,

1996.

ADDRESSES: Service information that

applies to this AD may be obtained from

The New Piper Aircraft, Inc., 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, Attention: Rules Docket 90–

CE–60–AD, 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, Campus Building, 1701

Columbia Avenue, suite 2–160, College

Park, Georgia 30337–2748; telephone

(404) 305–7362; facsimile (404) 305–

7348.

SUPPLEMENTARY INFORMATION:

Events Leading to the AD

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to include an AD that would

apply to Piper Models PA31, PA31–300,

PA31- 325, and PA31–350 airplanes was

published in the Federal Register on

January 31, 1996 (61 FR 3338). The

action proposed to supersede AD 80–

22–04 with a new AD that would

require inspecting (one-time) the upper

section of the FS 317.75 bulkhead for

cracks in accordance with Piper Service

Bulletin No. 636A, dated August 26,

1980, and accomplishing one of the

following, as applicable:

—If any crack is found, incorporating

Piper Kit 764–028 in accordance with

the instructions to that kit, revised

June 18, 1990; or

—If no crack is found, incorporating

Piper Kit 763–917 in accordance with

the instructions to that kit, revised

June 18, 1990.

Cracks found on airplanes in

compliance with the inspection

requirements of AD 80–22–04 prompted

the proposal.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the
Federal Register / Vol. 61, No. 110 / Thursday, June 6, 1996 / Rules and Regulations 28733

proposed rule or the FAA’s

determination of the cost to the public.

After careful review of all available

information related to the subject

presented above, 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

and will not add any additional burden

upon the public than was already

proposed.

Cost Impact

The FAA estimates that 2,810

airplanes in the U.S. registry will be

affected by this AD, that it will take

approximately 12 workhours (average of

8 workhours for Kit 763–917 and 16

workhours for Kit 764–028) per airplane

to accomplish the required installation,

and that the average labor rate is

approximately $60 an hour. Parts cost

approximately $300 per airplane. Based

on these figures, the total cost impact of

this AD on U.S. operators is estimated

to be $2,866,200 or $1,020 per airplane.

This figure is based on the assumption

that no affected airplane owner/operator

has accomplished the required

installation.

Piper has informed the FAA that

bulkhead reinforcement kits have been

distributed to equip at least 15 of the

affected airplanes. Assuming that each

of the kits has been incorporated on an

affected airplane, the cost impact of this

AD upon U.S. owners/operators of the

affected airplanes will be reduced by

$15,300 from $2,866,200 to $2,850,900.

Regulatory Impact

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, Incorporation by reference,

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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing Airworthiness Directive (AD)

80–22–04, Amendment 39–3943, and by

adding a new AD to read as follows:

96–12–12 The New Piper Aircraft, Inc.

(formerly Piper Aircraft Corporation):

Amendment 39–9654; Docket No. 90–

CE–60–AD. Supersedes AD 80–22–04,

Amendment 39–3943.

Applicability: The following model and

serial number airplanes, certificated in any

category, that do not have either Piper Kit

764–028 or Piper Kit 763–917 incorporated at

the Fuselage Station (FS) 317.75 bulkhead

area:

Models Serial Nos.

PA31, PA31–300, and

PA31–325.

31–2 through 31–

7912039.

PA31–350 .................. 31–5001 through 31–

7952071.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (c) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required within the next 100

hours time-in-service after the effective date

of this AD, unless already accomplished.

To prevent structural failure of the vertical

fin forward spar caused by cracks in the FS

317.75 bulkhead, which, if not detected and

corrected, could result in loss of control of

the airplane, accomplish the following:

(a) Inspect the upper section of the FS

317.75 bulkhead for cracks in accordance

with the INSTRUCTIONS section of Piper

Service Bulletin No. 636A, dated August 26,

1980.

(1) If any crack is found, prior to further

flight, incorporate Piper Kit 764–028 in

accordance with the instructions included

with that kit, revised June 18, 1990.

(2) If no crack is found, prior to further

flight, incorporate Piper Kit 763–917 in

accordance with the instructions included

with that kit, revised June 18, 1980.

(b) 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.

(c) 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), Campus Building,

1701 Columbia Avenue, suite 2–160, College

Park, Georgia 30337–2748. 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

Note 3: Alternative methods of compliance

approved in accordance with AD 80–22–04

(superseded by this action) are not

considered approved as alternative methods

of compliance with this AD.

(d) The inspection required by this AD

shall be done in accordance with Piper

Service Bulletin No. 636A, dated August 26,

1980. The installation required by this AD

shall be done in accordance with the

instructions to Piper Kit 764–028, revised

June 18, 1990, or Piper Kit 763–917, revised

June 18, 1990, as applicable. This

incorporation by reference was approved by

the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51. Copies may be obtained from The

New Piper Aircraft, Inc., 2926 Piper Drive,

Vero Beach, Florida 32960. Copies may be

inspected at the FAA, Central Region, Office

of the Assistant Chief Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri, or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(e) This amendment (39–9654) supersedes

AD 80–22–04, Amendment 39–3943.

(f) This amendment (39–9654) becomes

effective on July 16, 1996. Issued in Kansas

City, Missouri, on May 30, 1996.

John R. Colomy,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 96–14174 Filed 6–5–96; 8:45 am]

BILLING CODE 4910–13–U