Federal Register / Vol. 62, No. 148 / Friday, August 1, 1997 / Rules and Regulations 41255

proposed to require a one-time

inspection of the main landing gear

(MLG) retaining bolt to ensure that it is

installed correctly, and adjustments or

repairs, if necessary.

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.

Conclusion

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.

Cost Impact

There are approximately 598 Boeing

Model 767 series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 151 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 5 work

hours per airplane to accomplish the

required 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

$45,300, or $300 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

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

§39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

97–16–03 Boeing: Amendment 39–10093.

Docket 97–NM–25–AD.

Applicability: Model 767 series airplanes,

line positions 1 through 600 inclusive, except

line positions 579 and 586; 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 aft-acting landing gear trunnion

loads from being transferred to the main

landing gear (MLG) beam, and consequent

fracture and collapse of the MLG and loss of

control of the airplane on the ground,

accomplish the following:

(a) Within 500 flight hours or 300 flight

cycles after the effective date of this AD,

whichever occurs later, perform a one-time

inspection of the MLG retaining bolt to

ensure that it is installed correctly, in

accordance with Boeing Alert Service

Bulletin 767–32A0157, dated October 10,

1996. If the retaining bolt is incorrectly

installed, prior to further flight, make

adjustments or repairs in accordance with the

alert service bulletin.

(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, eattle

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, Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(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 actions shall be done in accordance

with Boeing Alert Service Bulletin 767–

32A0157, dated October 10, 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 Boeing

Commercial Airplane Group, P.O. Box 3707,

Seattle, Washington 98124–2207. 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

September 5, 1997.

Issued in Renton, Washington, on July 23,

1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–19902 Filed 7–31–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–18–AD; Amendment

39–10096; AD 97–16–05]

RIN 2120–AA64

Airworthiness Directives; Gulfstream

Aerospace Corporation Model G–159

(G–I) Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to all Gulfstream Model G–

159 (G–I) airplanes, that currently

requires repetitive inspections to detect

corrosion in the wing planks under the

bottom wing center fairings, and repair,

if necessary. This amendment requires

the installation of a protective paint

system which, when accomplished, will

allow the inspections to be conducted at

longer intervals. This amendment is
41256 Federal Register / Vol. 62, No. 148 / Friday, August 1, 1997 / Rules and Regulations

prompted by the development of a

modification that will improve the

corrosion resistance of the subject area.

The actions specified by this AD are

intended to detect and prevent

corrosion in the lower skins of the wing

center section. If corrosion in this area

remains unchecked, it could reduce the

integrity of the wing-to-fuselage fitting,

and consequently could lead to

separation of the wing from the

airplane.

DATES: Effective September 5, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of September

5, 1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Gulfstream Aerospace Corporation,

Technical Operations Department, P.O.

Box 2206, M/S D–10, Savannah, Georgia

31402–2206. 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 FAA, Atlanta

Aircraft Certification Office, Small

Airplane Directorate, Campus Building,

1701 Columbia Avenue, Suite 2–160,

College Park, Georgia; 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,

Airframe and Propulsion Branch, ACE–

117A, FAA, Atlanta Aircraft

Certification Office, Small Airplane

Directorate, Campus Building, 1701

Columbia Avenue, Suite 2–160, College

Park, Georgia 30337–2748; telephone

(404) 305–7362; fax (404) 305–7348.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 67–04–01,

amendment 39–1234 (36 FR 12688, July

3, 1971), which is applicable to all

Gulfstream Model G–159 (G–I)

airplanes, was published in the Federal

Register on March 6, 1997 (62 FR

10224). The action proposed to continue

to require the repetitive visual

inspections, specified in AD 67–04–01,

to detect corrosion of the wing planks

under the bottom wing center fairing

assemblies, and repair, if necessary.

For airplanes on which a protective

paint system had not been installed

previously, the action proposed to

require that the inspection continue to

be repeated at intervals of 6 months (26

weeks), until a protective paint system

is installed within 12 months. Once the

paint system is installed, the repetitive

inspections were proposed to be

required to continue, but the repetitive

interval would be extended to 18

months.

For airplanes on which a protective

paint system was installed previously,

the action proposed to extend the

currently-required repetitive inspection

interval of 12 months to 18 months.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 146

Gulfstream Model G–159 airplanes of

the affected design in the worldwide

fleet. The FAA estimates that 72

airplanes of U.S. registry will be affected

by this AD.

The inspections that are currently

required by AD 67–04–01, and those

that are required by this action, take

approximately 40 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

required inspection actions on U.S.

operators is estimated to be $172,800, or

$2,400 per airplane, per inspection.

The installation of the protective

paint system that is required by this AD

action will take approximately 30 work

hours per airplane to accomplish, at an

average labor rate of $60 per work hour.

Required materials will cost

approximately $100 per airplane. Based

on these figures, the cost impact of this

requirement of this AD on U.S.

operators is estimated to be $136,800, or

$1,900 per airplane.

The cost impact figures discussed

above are 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

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

§39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–1234 (36 FR

12688, July 3, 1971), and by adding a

new airworthiness directive (AD),

amendment 39–10096, to read as

follows:

97–16–05 Gulfstream Aerospace

Corporation: Amendment 39–10096.

Docket 97–NM–18–AD. Supersedes AD

67–04–01, Amendment 39–1234.

Applicability: All Model G–159 (G–I)

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

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 (d)(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.
Federal Register / Vol. 62, No. 148 / Friday, August 1, 1997 / Rules and Regulations 41257

To detect and prevent corrosion in the

lower skins of the wing center section, which

could reduce the integrity of the wing-tofuselage fitting and consequently could lead

to separation of the wing from the airplane,

accomplish the following:

(a) For all airplanes: Within 4 weeks after

July 3, 1971 (the effective date of AD 67–04–

01, amendment 39–1234), remove the bottom

wing center fairings having part numbers (P/

N) 159W10400–121 and 159W10401–121, or

use an FAA-approved equivalent method, to

perform a visual inspection to detect

corrosion of the wing planks under these

fairings.

Note 2: Paragraph (a) of this AD merely

restates the actions previously required by

AD 67–04–01, amendment 39–1234. As

allowed by the phrase, ‘‘unless accomplished

previously,’’ if those requirements of AD 67–

04–01 have already been accomplished, this

AD does not require that those actions be

repeated.

Note 3: Care must be exercised when

removing the fairings, since the attaching

rivets go into the pressure vessel. Use caution

not to enlarge rivet holes when removing

rivets. When reinstalling the fairings, an

adequate type fastener and sealant must be

used.

Note 4: Grumman Service Newsletter,

Volume 166, dated August-September 1966,

pertains to this subject.

(b) For airplanes on which a protective

paint system has not been installed in

accordance with Grumman Gulfstream I

Aircraft Service Change No. 190, dated June

28, 1971: Accomplish paragraphs (b)(1) and

(b)(2) of this AD. As of the effective date of

this AD, the inspections required by this

paragraph shall be accomplished in

accordance with Grumman Gulfstream I

Aircraft Service Change No. 190, dated June

28, 1971.

Note 5: The repeated inspection referred to

in this paragraph is the same inspection

previously required by AD 67–04–01.

Paragraph (b)(1) of this AD merely restates

the requirement of AD 67–04–01 to repeat the

inspection at intervals of 6 months.

Paragraph (b)(2) permits the reinspection

interval to be extended to 18 months once the

specified protective paint system is installed.

(1) As a result of the inspection required

by paragraph (a) of this AD:

(i) If no corrosion is detected, repeat the

inspection thereafter at intervals not to

exceed 6 months (26 weeks) until the actions

specified in paragraph (b)(2) of this AD are

accomplished.

(ii) If any corrosion is detected, prior to

further flight, either repair the corroded part

with an FAA-approved repair; or replace the

corroded part with a new or serviceable part

of the same part number; or replace the

corroded part with a part approved by the

FAA. Thereafter, continue to perform the

inspection at intervals not to exceed 6

months (26 weeks) until paragraph (b)(2) of

this AD is accomplished.

(2) Within 12 months after the effective

date of this AD, install the protective paint

system in accordance with Grumman

Gulfstream I Aircraft Service Change No. 190,

dated June 28, 1971. After installation,

continue to perform the inspection required

by this paragraph at intervals not to exceed

18 months.

(c) For airplanes on which a protective

paint system has been installed previously in

accordance with Grumman Gulfstream I

Aircraft Service Change

No. 190, dated June 28, 1971: Accomplish

paragraphs (c)(1) and (c)(2) of this AD. As of

the effective date of this AD, the inspections

required by this paragraph shall be

accomplished in accordance with Grumman

Gulfstream I Aircraft Service Change No. 190,

dated June 28, 1971.

Note 6: The repeated inspection referred to

in this paragraph is the same inspection

previously required by AD 67–04–01.

Paragraph (c)(1) of this AD merely restates

the requirement of AD 67–04–01 to repeat the

inspection at intervals of 12 months.

Paragraph (c)(2) permits the reinspection

interval to be extended to 18 months.

(1) As a result of the inspection required

by paragraph (a) of this AD:

(i) If no corrosion is detected, repeat the

inspection thereafter at intervals not to

exceed 12 months until paragraph (c)(2) of

this AD is accomplished.

(ii) If any corrosion is detected, prior to

further flight, either repair the corroded part

with an FAA-approved repair; or replace the

corroded part with a new or serviceable part

of the same part number; or replace the

corroded part with a part approved by the

FAA. Thereafter, continue to perform the

inspection at intervals not to exceed 12

months until paragraph (c)(2) of this AD is

accomplished.

(2) Within 18 months since the last

inspection accomplished in accordance with

paragraph (c)(1) of this AD (i.e., the last

inspection accomplished in accordance with

AD 67–04–01), repeat the inspection

specified in paragraph (c)(1) of this AD.

(i) If no corrosion is detected, repeat the

inspection thereafter at intervals not to

exceed 18 months.

(ii) If any corrosion is detected, prior to

further flight, repair in accordance with the

service change. After repair, continue to

perform the inspection at intervals not to

exceed 18 months.

(d)(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, Atlanta

Aircraft Certification Office (ACO), FAA,

Small 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, Atlanta ACO.

(2) Alternative methods of compliance,

approved previously in accordance with AD

67–04–01, amendment 39–1234, are

approved as alternative methods of

compliance with this AD.

Note 7: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

(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) The actions shall be done in accordance

with Grumman Gulfstream I Aircraft

Service Change No. 190, dated June 28,

1971. 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 Gulfstream Aerospace Corporation,

Technical Operations Department, P.O. Box

2206, M/S D–10, Savannah, Georgia 31402–

2206. Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

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

FAA, Atlanta Aircraft Certification Office,

Small Airplane Directorate, Campus

Building, 1701 Columbia Avenue, Suite 2–

160, College Park, Georgia; or at the Office of

the Federal Register, 800 North Capitol

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

(g) This amendment becomes effective on

September 5, 1997.

Issued in Renton, Washington, on July 25,

1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–20129 Filed 7–31–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–NM–228–AD; Amendment

39–10097; AD 97–16–06]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Airbus Model A300–

600 series airplanes, that requires an

inspection to detect cracks of certain

attachment holes; and installation of a

new fastener and follow-on inspections

or repair, if necessary. This amendment

is prompted by reports of fatigue

cracking found on the forward fitting of

frame 47 at the level of the last fastener

of the external angle fitting. The actions

specified by this AD are intended to

prevent such fatigue cracking, which

could result in reduced structural

integrity of the airframe.

DATES: Effective September 5, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of September

5, 1997.

ADDRESSES: The service information

referenced in this AD may be obtained