26780 Federal Register / Vol. 61, No. 104 / Wednesday, May 29, 1996 / Rules and Regulations

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–11–11 McDonnell Douglas: Amendment

39–9636. Docket 95–NM–145–AD.

Applicability: All Model DC–9–10, –20,

–30, –40, –50, and C–9 (military) series

airplanes, certificated in any category.

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 (b)(1) 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 fatigue-related cracking, which

could compromise the structural integrity of

the airplane, accomplish the following:

(a) Prior to the accumulation of 40,000 total

landings, or within 3,000 landings after the

effective date of this AD, whichever occurs

later, perform a high frequency eddy current

(HFEC) inspection to detect cracking in the

nose skin of the fuselage, in accordance with

McDonnell Douglas DC–9 Service Bulletin

53–262, dated October 11, 1994.

(1) If no cracking is detected, accomplish

either paragraph (a)(1)(i) or (a)(1)(ii) of this

AD, in accordance with the service bulletin.

(i) Repeat the HFEC inspection thereafter at

intervals not to exceed 4,000 landings; or

(ii) Accomplish the modification of the

upper nose skin of the cockpit fuselage in

accordance with the service bulletin. Prior to

the accumulation of 60,000 landings after

accomplishment of this modification,

perform a visual inspection of the upper nose

skin of the cockpit fuselage in accordance

with the service bulletin. Repeat the visual

inspection thereafter at intervals not to

exceed 25,000 landings.

(2) If any cracking is detected and it is

within the repair limits specified in the

service bulletin, prior to further flight, repair

the cracked nose skin in accordance with the

service bulletin. Prior to the accumulation of

60,000 landings after accomplishment of this

repair, perform a visual inspection to detect

cracking of the repair; and prior to further

flight, repair any cracking found during this

inspection; in accordance with a method

approved by the Manager, Los Angeles

Aircraft Certification Office (ACO), FAA,

Transport Airplane Directorate.

(3) If any cracking is detected and it is

beyond the repair limits specified in the

service bulletin, prior to further flight, repair

the cracked nose skin in accordance with a

method approved by the Manager, Los

Angeles ACO.

(b)(1) 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 ACO. 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.

(b)(2) Alternative methods of compliance,

approved in accordance with AD 94–03–01,

amendment 39–8907, are approved as

alternative methods of compliance with

paragraphs (a)(2) and (a)(3) of this AD. This

approval only applies to repairs that are

subject to the requirements of this AD.

(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 inspections, modification, and

certain repairs shall be done in accordance

with McDonnell Douglas DC–9 Service

Bulletin 53–262, dated October 11, 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 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.

(e) This amendment becomes effective on

July 3, 1996.

Issued in Renton, Washington, on May 20,

1996.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–13231 Filed 5–28–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–CE–82–AD; Amendment 39–

9637; AD 96–11–12]

RIN 2120–AA64

Airworthiness Directives; Beech

Aircraft Corporation Model C90A

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Beech Aircraft

Corporation (Beech) Model C90A

airplanes equipped with an optional

Beech electric trim system or a Collins

autopilot system. This action requires

modifying the elevator electric trim tab

actuator assembly. Failure of the

elevator electric trim tab system on a

Beech Model C90A prompted the

proposed AD action. The actions

specified by the proposed AD are

intended to prevent possible failure of

the elevator electric trim tab system,

which, if not detected and corrected,

could cause loss of airplane

maneuverablity and possible loss of

control of the airplane.

DATES: Effective July 24, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 24,

1996.

ADDRESSES: Service information that

applies to this AD may be obtained from

Beech Aircraft Corporation, P.O. Box 85,

Wichita, Kansas 67201–0085. This

information may also be examined at

the Federal Aviation Administration

(FAA), Central Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket 95–CE–82–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:

Harvey E. Nero, Aerospace Engineer,

FAA, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100,

Mid-Continent Airport, Wichita, Kansas

67209; telephone (316) 946–4137;

facsimile (316) 946–4407.

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

Beech Aircraft Corporation (Beech)

Model C90A airplanes equipped with an

optional Beech electric trim system or a

Collins autopilot system was published

in the Federal Register on November 28,

1995 (60 FR 58583). The action

proposed to require procedures for

modifying the elevator electric trim tab

actuator assembly. Accomplishment of

this action will be in accordance with

Beech Service Bulletin (SB) No. 2631,

Issued: June 1995, Revised: September

1995.

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 related to the subject

presented above, the FAA has
Federal Register / Vol. 61, No. 104 / Wednesday, May 29, 1996 / Rules and Regulations 26781

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.

The FAA estimates that 300 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

6 workhours per airplane to accomplish

this action, and that the average labor

rate is approximately $60 an hour. Parts

are estimated to be $160 per airplane.

Based on these figures, the total cost

impact of this AD on U.S. operators is

estimated to be $156,000 or $520 per

airplane. Beech has informed FAA that

no parts have been distributed to

owners/operators for this modification;

therefore, this figure is based on the

assumption that no owners/operators

have accomplished the proposed

inspection and modification.

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 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive

(AD) to read as follows:

96–11–12. Beech Aircraft Corporation:

Amendment 39–9637; Docket No. 95–

CE–82–AD.

Applicability: The following Model C90A

Airplanes, certificated in any category, that

are equipped with an optional Beech electric

trim system or a Collins autopilot system:

(1) Serial numbers LJ–1111 through LJ–

1410 that were equipped at manufacture

assembly with a pin-type cable guard

actuator assembly (P/N 33–524023–51) on

the elevator electric trim tab actuator

assembly.

(2) All serial numbers (except LJ–1 through

LJ–1110) equipped with a pin-type cable

guard actuator assembly (P/N 33–524023–51)

installed through field approval.

Note 1: Steps 1 through 4 of the

ACCOMPLISHMENT INSTRUCTIONS

section of Beech Service Bulletin (SB) No.

2631, Issued: June 1995, Revised: September

1995, provide procedures for determining

which assembly is installed.

Note 2: 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 as follows, unless

already accomplished:

(1) Within 150 hours time-in-service (TIS)

after the effective date of this AD; or

(2) Upon installation of an optional Beech

elevator electric trim tab system or a Collins

autopilot system, whichever occurs first.

To prevent possible failure of the optional

Beech electric trim system or the Collins

autopilot system, which, if not detected and

corrected, could cause loss of airplane

maneuverability and possible loss of control

of the airplane, accomplish the following:

(a) Modify all elevator electric trim tab

actuator assemblies, part number (P/N) 33–

524023–51 to the P/N 33–524023–77 or P/N

33–524023–79 level, by accomplishing the

procedures in the ACCOMPLISHMENT

INSTRUCTIONS section of Beechcraft

Mandatory Service Bulletin SB No. 2631,

Issued: June 1995, Revised: September 1995.

(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 initial or repetitive

compliance times that provides an equivalent

level of safety may be approved by the

Manager, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 67209.

The request shall be forwarded through an

appropriate FAA Maintenance Inspector,

who may add comments and then send it to

the Manager, Wichita Aircraft Certification

Office.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita Aircraft

Certification Office.

(d) The modification required by this AD

shall be done in accordance with Beechcraft

Mandatory Service Bulletin No. 2631, Issued:

June 1995, Revised: September 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 Beech

Aircraft Corporation, P.O. Box 85, Wichita,

Kansas 67201–0085. 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., 7th Floor, suite 700,

Washington, DC.

(e) This amendment (39–9637) becomes

effective on June 24, 1996.

Issued in Kansas City, Missouri, on May

22, 1996.

Bobby Sexton,

Action Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 96–13273 Filed 5–28–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Airspace Docket No. 96–ANE–12]

Amendment to Class E Airspace;

Pittsfield, MA

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Direct final rule; request for

comments.

SUMMARY: This action revises the Class

E airspace area at Pittsfield, MA (PSF)

to provide for adequate controlled

airspace for those aircraft using the GPS

RWY 8 Instrument Approach Procedure

to Pittsfield Municipal Airport.

DATES: Effective 0901 UTC, August 15,

1996.

Comments for inclusion in the Rules

Docket must be received on or before

June 28, 1996.

ADDRESSES: Send comments on the

proposal to: Manager, Operations