5280 Federal Register / Vol. 61, No. 29 / Monday, February 12, 1996 / Rules and Regulations

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 a new airworthiness directive

(AD) to read as follows:

96–03–03 Fairchild Aircraft: Amendment

39–9499; Docket No. 95–CE–17–AD.

Applicability: Models SA226–T, SA226–

T(B), SA226–AT, SA226–TC, SA227–TT,

SA227–AT, SA227–AC, SA227–BC, SA227–

CC, and SA227–DC airplanes (all serial

numbers), 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 (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 the power control cable from

disconnecting from the lever attach point

clevis, which could result in engine

shutdown and subsequent loss of control of

the airplane, accomplish the following:

(a) Replace the nuts that attach the power

control cable to the lever attach point clevis

with nuts that have safety wire holes, safetywire the power control cable to the lever

attach clevis, inspect to assure that the power

cable is securely attached to the power

control cable bracket, and correct any

attachment problems. Accomplish these

actions in accordance with the following

service bulletins, as applicable:

(1) Fairchild Service Bulletin (SB) 226–76–

009, dated January 6, 1995;

(2) Fairchild SB 227–76–004, dated January

6, 1995; or

(3) Fairchild SB CC7–76–001, dated

January 6, 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 compliance time that

provides an equivalent level of safety may be

approved by the Manager, Fort Worth

Airplane Certification Office (ACO), FAA,

2601 Meacham Boulevard, Fort Worth, Texas

76137–0150. The request shall be forwarded

through an appropriate FAA Maintenance

Inspector, who may add comments and then

send it to the Manager, Fort Worth ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Fort Worth ACO.

(d) The replacement required by this AD

shall be done in accordance with Fairchild

Service Bulletin 226–76–009; Fairchild

Service Bulletin 227–76–004; or Fairchild

Service Bulletin CC7–76–001, all Issued:

January 6, 1995, 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

Fairchild Aircraft, P.O. Box 790490, San

Antonio, Texas 78279–0490. 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 (39–9499) becomes

effective on March 15, 1996.

Issued in Kansas City, Missouri, on January

23, 1996.

John R. Colomy,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 96–1574 Filed 2–9–96;8:45am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–238–AD; Amendment

39–9503; AD 96–03–06]

Airworthiness Directives; Jetstream

ATP Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Jetstream ATP

airplanes, that requires inspections to

detect fatigue cracking and corrosion in

the gussets of the rear passenger door

and rear baggage door apertures, and

replacement of the gussets, if necessary.

This amendment is prompted by fatigue

tests which indicated that fatigue

cracking and corrosion can occur in

these gussets. The actions specified by

this AD are intended to prevent

degradation of the structural integrity of

the fuselage pressure vessel due to the

problems associated with cracking and

corrosion in the gussets of the rear

passenger door and rear baggage door

apertures.

DATES: Effective March 13, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 13,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Jetstream Aircraft, Inc., P.O. Box

16029, Dulles International Airport,

Washington, DC 20041–6029. 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) 227–2747; 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 Jetstream

ATP airplanes was published in the

Federal Register on October 13, 1995

(60 FR 53312). That action proposed to

require a one-time detailed visual

inspection for fatigue cracking and

corrosion in the gussets of the rear

passenger door and the rear baggage

door apertures. That action also

proposed replacement of cracked

gussets, and either replacement or repair

of corroded gussets.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

The FAA estimates that 10 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 8

work hours per airplane to accomplish

the required inspection actions, and that

the average labor rate is $60 per work

hour. Based on these figures, the cost

impact of the AD on U.S. operators is

estimated to be $4,800, or $480 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.

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
Federal Register / Vol. 61, No. 29 / Monday, February 12, 1996 / Rules and Regulations 5281

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 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:

96–03–06 Jetstream Aircraft Limited

(Formerly British Aerospace Commercial

Aircraft, Ltd.): Amendment 39–9503.

Docket 94–NM–238–AD.

Applicability: Model ATP airplanes;

having serial numbers 2002 through 2012

inclusive; and 2019 through 2022 inclusive,

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 use the authority

provided in paragraph (c) of this AD to

request approval from the FAA. This

approval may address either no action, if the

current configuration eliminates the unsafe

condition; or different actions necessary to

address the unsafe condition described in

this AD. Such a request should include an

assessment of the effect of the changed

configuration on the unsafe condition

addressed by this AD. In no case does the

presence of any modification, alteration, or

repair remove any airplane from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent degradation of the structural

integrity of the fuselage pressure vessel due

to the problems associated with cracking and

corrosion in the gussets of the rear passenger

door and rear baggage door apertures,

accomplish the following:

(a) Prior to the accumulation of 12,000 total

landings or within 1,500 landings after the

effective date of this AD, whichever occurs

later, perform a detailed visual inspection to

detect cracks and corrosion of the gussets of

the rear passenger door aperture, in

accordance with Jetstream Service Bulletin

ATP–53–29, dated October 31, 1994.

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

flight, replace the gusset in accordance with

the service bulletin.

(2) If any corrosion is found, prior to

further flight, either replace the gusset in

accordance with the service bulletin, or

repair the gusset in accordance with the

Structural Repair Manual, chapter 53–10–12.

(b) Prior to the accumulation of 15,000

total landings or within 1,500 landings after

the effective date of this AD, whichever

occurs later, perform a detailed visual

inspection to detect cracks and corrosion of

the gussets of the rear baggage door aperture,

in accordance with Jetstream Service Bulletin

ATP–53–29, dated October 31, 1994.

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

flight, replace the gusset in accordance with

the service bulletin.

(2) If any corrosion is found, prior to

further flight, either replace the gusset in

accordance with the service bulletin, or

repair the gusset in accordance with the

Structural Repair Manual, chapter 53–10–12.

(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,

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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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 Jetstream Service Bulletin ATP–53–29,

dated October 31, 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 Jetstream Aircraft, Inc., P.O.

Box 16029, Dulles International Airport,

Washington, DC 20041–6029. 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.

(f) This amendment becomes effective on

March 13, 1996.

Issued in Renton, Washington, on January

23, 1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–1519 Filed 2–9–96; 8:45am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–39–AD; Amendment

39–9502; AD 96–03–05]

Airworthiness Directives; McDonnell

Douglas Model MD–11 Series

Airplanes and Model DC–10–30, DC–

10–40, and KC–10A (Military) Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model MD–11 series airplanes

and Model DC–10–30, DC–10–40, and

KC–10A (military) airplanes. For Model

MD–11 series airplanes, the AD requires

an inspection to determine the serial

number of the forward trunnion bolts on

the main landing gear (MLG), and

rework or replacement of the bolts, if

necessary. For Model DC–10–30, DC–

10–40, and KC–10A (military) airplanes,

the AD requires an inspection for

evidence of missing chrome and for

corrosion on the chrome surfaces, or

verification that the forward trunnion

bolts have been chrome plated in a

specific manner; and rework or

replacement of the bolts, if necessary.

This amendment is prompted by reports

of chrome flaking on the bearing surface

of the trunnion bolts due to improper

cleaning of the base material prior to

chrome plating. The actions specified by

this AD are intended to prevent

premature failure of the trunnion bolts

and subsequent collapse of the MLG as

a result of severe corrosion on the

bearing surface and in the mechanical

fuse due to chrome flaking.

DATES: Effective March 13, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 13,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained