24690 Federal Register / Vol. 61, No. 96 / Thursday, May 16, 1996 / Rules and Regulations

the effective date of this AD, whichever

occurs later, perform either an ultrasonic

inspection or an eddy current inspection, as

applicable, to detect cracks of the upper aft

mating bolt hole of the wing pylon truss

fittings, in accordance with McDonnell

Douglas DC–10 Service Bulletin 54–108,

dated February 9, 1995.

(1) If no cracks are detected, repeat the

inspections in accordance with paragraph

(b)(1)(i) or (b)(1)(ii), as applicable:

(i) If inspecting using ultrasonic

techniques, repeat the inspection at intervals

not to exceed 10,000 landings.

(ii) If inspecting using eddy current

techniques, repeat the inspection at intervals

not to exceed 15,000 landings.

(2) Accomplishment of the actions

specified in paragraphs (b)(2)(i), (b)(2)(ii),

and (b)(2)(iii) constitutes terminating action

for the repetitive inspections required by

paragraph (b)(1) of this AD:

(i) Accomplish the preventative

modification in accordance with Condition 1

(bushing not installed), Option III, or

Condition 2 (bushing installed), Option II, of

the service bulletin, as applicable. And

(ii) Prior to the accumulation of 18,000

total landings on the pylon truss fitting

following accomplishment of the

modification, perform an ultrasonic

inspection to detect cracks of the upper aft

mating bolt hole of the wing pylon truss

fittings, in accordance with the service

bulletin. And

(iii) Thereafter, repeat the ultrasonic

inspection at intervals not to exceed 10,000

landings on the pylon truss fitting.

(3) If any crack is found in the pylon truss

fitting during any inspection required by this

paragraph, prior to further flight, repair it in

accordance with the service bulletin. At the

times specified in the service bulletin,

perform follow-on actions in accordance with

the service bulletin. In all cases, where the

service bulletin indicates ‘‘contact Douglas

for disposition,’’ the repair must be

accomplished in accordance with a method

approved by the Manager, Los Angeles

Aircraft Certification Office (ACO), FAA,

Transport Airplane Directorate.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Los

Angeles Aircraft Certification Office (ACO),

FAA, Transport Airplane Directorate.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Los Angeles ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(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) The actions shall be done in accordance

with McDonnell Douglas DC–10 Service

Bulletin 54–108, dated February 9, 1995.

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 McDonnell Douglas Corporation, 3855

Lakewood Boulevard, Long Beach, California

90846, Attention: Technical Publications

Business Administration, Department C1–

L51 (2–60). Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington; or at

the FAA, Los Angeles Aircraft Certification

Office, Transport Airplane Directorate, 3960

Paramount Boulevard, Lakewood, California;

or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(f) This amendment becomes effective on

June 20, 1996.

Issued in Renton, Washington, on May 9,

1996.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–12147 Filed 5–15–96; 8:45 am]

BILLING CODE 4910–13–M

14 CFR Part 39

[Docket No. 95–NM–198–AD; Amendment

39–9625; AD 96–10–18]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320–111, –211, –212, and –231 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A320–111, –211, –212, and –231 series

airplanes, that requires removing the

existing forward pintle nut and cross

bolt on the main landing gear (MLG),

and installing a new nylon spacer and

cross bolt and nut. This amendment is

prompted by results of fatigue testing

which revealed that the cross bolt and

nut in the forward pintle pin of the MLG

were damaged due to fatigue cracking.

The actions specified by this AD are

intended to prevent such fatigue

cracking, which could result in collapse

of the MLG.

DATES: Effective June 20, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 20,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tim

Backman, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Airbus

Model A320 series airplanes was

published in the Federal Register on

March 6, 1996 (61 FR 8896). That action

proposed to require removing the

existing forward pintle nut and cross

bolt on the MLG; and installing a new

nylon spacer and cross bolt and nut.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

Both commenters support the

proposed rule.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 90 Airbus

Model A320–111, –211, –212, and –231

series airplanes of U.S. registry will be

affected by this AD, that it will take

approximately 1 work hour per airplane

to accomplish the required actions, and

that the average labor rate is $60 per

work hour. Required parts will be

supplied by the parts manufacturer at

no cost to the operators. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be $5,400,

or $60 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

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
Federal Register / Vol. 61, No. 96 / Thursday, May 16, 1996 / Rules and Regulations 24691

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from 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

adding the following new airworthiness

directive:

96–10–18 Airbus: Amendment 39–9625.

Docket 95–NM–198–AD.

Applicability: Model A320–111, –211,

–212, and –231 series airplanes, on which

Airbus Modification 23573 (Airbus Service

Bulletin A320–32–1119, Revision 1, dated

June 13, 1994), has not been installed;

certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 (b) 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 as indicated, unless

accomplished previously.

To prevent collapse of the main landing

gear (MLG) during landing, due to failure of

the forward pintle pin cross bolt, accomplish

the following:

(a) Remove the existing forward pintle nut

and cross bolt; and install a new nylon spacer

and post-mod cross bolt and nut of the MLG,

in accordance with Airbus Service Bulletin

A320–32–1119, Revision 1, dated June 13,

1994, at the later of the times specified in

paragraphs (a)(1) and (a)(2) of this AD.

(1) Prior to the accumulation of 20,000

total landings, or at the next main landing

gear overhaul, whichever occurs first.

(2) Within 500 landings after the effective

date of this AD.

Note 2: The Airbus service bulletin

references Dowty Aerospace Service Bulletin

200–32–194, Revision 1, dated October 4,

1993, as an additional source of service

information for accomplishment of these

procedures.

(b) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(c) 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.

(d) The removal and installation shall be

done in accordance with Airbus Service

Bulletin A320–32–1119, Revision 1, dated

June 13, 1994. 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 Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street NW., suite 700, Washington,

DC.

(e) This amendment becomes effective on

June 20, 1996.

Issued in Renton, Washington, on May 9,

1996.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–12146 Filed 5–15–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 90–CE–61–AD; Amendment 39–

9620; AD 96–10–13]

RIN 2120–AA64

Airworthiness Directives; the New

Piper Aircraft, Inc. (Formerly Piper

Aircraft Corporation) Models PA31T,

PA31T1, PA31T2, and PA31T3

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

Airworthiness Directive (AD) 84–08–06,

which currently requires the following

on certain The New Piper Aircraft, Inc.

(Piper) Models PA31T, PA31T1,

PA31T2, and PA31T3 airplanes:

repetitively inspecting the fuselage

station (FS) 332 bulkhead for cracks,

and reinforcing or replacing the FS 332

bulkhead if cracks are found. The

Federal Aviation Administration’s

policy on aging commuter-class aircraft

is to eliminate or, in certain instances,

reduce the number of certain repetitive

short-interval inspections when

improved parts or modifications are

available. This action retains the current

repetitive inspections contained in AD

84–08–06, and requires incorporating a

stabilizer forward spar attachment

bulkhead reinforcement kit or installing

a reinforced bulkhead assembly as

terminating action for the repetitive

inspection requirement. The actions

specified in this AD are intended to

prevent structural failure of the

horizontal stabilizer and the aft fuselage

attachment caused by cracks in the FS

332 bulkhead, which, if not detected

and corrected, could result in loss of

control of the airplane.

DATES: Effective June 27, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 27,

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–61–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,