34530 Federal Register / Vol. 66, No. 126 / Friday, June 29, 2001 / Rules and Regulations

Seattle ACO, as required by this paragraph,

the Manager’s approval letter must

specifically reference this AD.

Alternative Methods of Compliance

(g) 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, Seattle

ACO. 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 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(h) 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.

Incorporation by Reference

(i) Except as provided by paragraph (f) of

this AD, the actions shall be done in

accordance with Boeing Service Bulletin

747–57A2310, Revision 1, dated November

23, 1999; or Boeing Service Bulletin 747–

57A2310, Revision 2, dated February 22,

2001; 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 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.

Effective Date

(j) This amendment becomes effective on

August 3, 2001.

Issued in Renton, Washington, on June 20,

2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–16049 Filed 6–28–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–306–AD; Amendment

39–12298; AD 2000–03–20 R1]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 B4–601, B4–603, B4–620, B4–

605R, B4–622R, and F4–605R

(Collectively Called A300–600) Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment revises an

existing airworthiness directive (AD),

applicable to all Airbus Model A300

B4–601, B4–603, B4–620, B4–605R, B4–

622R, and F4–605R (collectively called

A300–600) series airplanes, that

currently requires repetitive ultrasonic

inspections to detect cracks on the

forward fittings in the radius of frame 40

adjacent to the tension bolts in the

center section of the wings, and various

follow-on actions. That AD was

prompted by reports of cracking due to

fatigue-related stress in the radius of

frame 40 adjacent to the tension bolts at

the center/outer wing junction. The

actions specified by that AD are

intended to detect and correct fatigue

cracking on the forward fittings in the

radius of frame 40 adjacent to the

tension bolts in the center section of the

wings, which could result in reduced

structural integrity of the wings. This

amendment removes airplanes from the

applicability of the existing AD.

DATES: Effective August 3, 2001.

The incorporation by reference of

certain publications, as listed in the

regulations, was approved previously by

the Director of the Federal Register as of

March 28, 2000 (65 FR 8642, February

22, 2000).

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:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by revising AD 2000–03–20, amendment

39–11580 (65 FR 8642, February 22,

2000), which is applicable to Airbus

Model A300 B4–601, B4–603, B4–620,

B4–605R, B4–622R, and F4–605R

(collectively called A300–600) series

airplanes, was published in the Federal

Register on January 10, 2001 (66 FR

1919). The action proposed to continue

to require repetitive ultrasonic

inspections to detect cracks on the

forward fittings in the radius of frame 40

adjacent to the tension bolts in the

center section of the wings, and various

follow-on actions. The action also

proposed to remove Model A300 F4–

622R from the applicability of the

existing AD.

Comments

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

Since this AD merely deletes Model

A300 F4–622R airplanes from the

applicability of AD 2000–03–02, it adds

no additional costs, and will require no

additional work to be performed by

affected operators. The current costs

associated with this AD are reiterated in

their entirety (as follows) for the

convenience of affected operators:

The FAA estimates that 35 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 2

work hours per airplane (1 work hour

per side) to accomplish the required

ultrasonic inspection, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the required inspection on U.S.

operators is estimated to be $4,200, or

$120 per airplane, per inspection cycle.

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 cost impact

figures discussed in Ad rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

Federal Register / Vol. 66, No. 126 / Friday, June 29, 2001 / Rules and Regulations 34531

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

Regulatory Impact

The regulations adopted herein will

not have a substantial direct effect 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, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

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 39–11580 (65 FR

8642, February 22, 2000), and by adding

a new airworthiness directive (AD),

amendment 39–12298, to read as

follows:

2000–03–20 R1 Airbus Industries:

Amendment 39–12298. Docket 2000–

NM–306–AD. Revises AD 2000–03–20,

Amendment 39–11580.

Applicability: All Model A300 B4–601,

B4–603, B4–620, B4–605R, B4–622R, and

F4–605R 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 (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.

To detect and correct fatigue cracking on

the forward fittings in the radius of frame 40

adjacent to the tension bolts in the center

section of the wings, which could result in

reduced structural integrity of the wings,

accomplish the following:

Inspections and Corrective Actions

(a) Perform an ultrasonic inspection to

detect cracking on the forward fittings in the

radius of frame 40 adjacent to the tension

bolts in the center section of the wings, in

accordance with Airbus Service Bulletin

A300–57–6062, Revision 02, dated January

29, 1997, at the applicable time specified in

either paragraph (a)(1) or (a)(2) of this AD.

(1) For airplanes that have accumulated

fewer than 9,100 total landings or 22,300

total flight hours as of March 28, 2000 (the

effective date of AD 2000–03–20, amendment

39–11580): Inspect at the later of the times

specified in either paragraph (a)(1)(i) or

(a)(1)(ii) of this AD.

(i) Prior to the accumulation of 7,250 total

landings or 17,700 total flight hours,

whichever occurs first.

(ii) Within 1,500 landings after March 28,

2000.

(2) For airplanes that have accumulated

9,100 total landings or more and 22,300 total

flight hours or more as of March 28, 2000:

Inspect within 750 landings after March 28,

2000.

Note 2: Inspections that were

accomplished prior to March 28, 2000, in

accordance with Airbus Service Bulletin

A300–57–6062, Revision 1, dated July 23,

1995, are considered acceptable for

compliance with paragraph (a) of this AD.

(b) If no crack is detected during the

inspection required by paragraph (a) of this

AD, repeat the ultrasonic inspection required

by that paragraph thereafter at intervals not

to exceed 6,500 landings or 16,000 flight

hours, whichever occurs first; in accordance

with Airbus Service Bulletin A300–57–6062,

Revision 02, dated January 29, 1997.

(c) If any crack is detected during any

inspection required by paragraph (a) or (b) of

this AD, prior to further flight, install an

access door, and perform an eddy current

inspection to confirm the presence of a crack;

in accordance with Airbus Service Bulletin

A300–57–6062, Revision 02, dated January

29, 1997. Accomplishment of this eddy

current inspection terminates the repetitive

inspection requirement of paragraph (b) of

this AD.

(1) If no crack is detected during the eddy

current inspection, repeat the eddy current

inspection, in accordance with the service

bulletin, thereafter at intervals not to exceed

6,500 landings or 16,000 flight hours,

whichever occurs first.

(2) If any crack is detected during any eddy

current inspection performed in accordance

with paragraph (c) or (c)(1) of this AD, prior

to further flight, blend out the crack and

repeat the eddy current inspection in

accordance with the service bulletin.

(i) If the eddy current inspection performed

after the blend-out shows that the crack has

been removed, and if the blend-out is equal

to or less than 50 millimeters (mm) long and

equal to or less than 2 mm deep, thereafter

repeat the eddy current inspection at

intervals not to exceed 2,800 landings or

7,000 flight hours, whichever occurs first.

(ii) If the eddy current inspection

performed after the blend-out shows that the

crack has not been removed, or if the blendout is more than 50 mm long or more than

2 mm deep, prior to further flight, repair in

accordance with a method approved by the

Manager, International Branch, ANM–116,

FAA, Transport Airplane Directorate; or the

Direction Ge ́ne ́rale de l’Aviation Civile (or its

delegated agent).

Alternative Methods of Compliance

(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,

International Branch, ANM–116. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

(2) Operators may request an extension to

the compliance times of this AD in

accordance with the ‘‘adjustment-for-range’’

formula found in Paragraph 1.B.(5) of Airbus

Service Bulletin A300–57–6062, Revision 02,

dated January 29, 1997; and provided in

A300–600 Maintenance Review Board,

Section 5, Paragraph 5.4. The average flight

time per flight cycle (landing) in hours used

in this formula should be for an individual

airplane. Average flight time for a group of

airplanes may be used if all airplanes of the

group have flight times differing by no more

than 10 percent. If compliance times are

based on the average flight time for a group

of airplanes, the flight times for individual

airplanes of the group must be included for

FAA review.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(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.

34532 Federal Register / Vol. 66, No. 126 / Friday, June 29, 2001 / Rules and Regulations

Incorporation by Reference

(f) Except as provided by paragraph

(c)(2)(ii) of this AD, the actions shall be done

in accordance with Airbus Service Bulletin

A300–57–6062, Revision 02, dated January

29, 1997. This incorporation by reference was

approved previously by the Director of the

Federal Register as of March 28, 2000 (65 FR

8642, February 22, 2000). 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.

Note 4: The subject of this AD is addressed

in French airworthiness directive 1995–063–

177(B) R4, dated July 12, 2000.

Effective Date

(g) This amendment becomes effective on

August 3, 2001.

Issued in Renton, Washington, on June 21,

2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–16202 Filed 6–28–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–83–AD; Amendment

39–12191; AD 2001–08–13]

RIN 2120–AA64

Airworthiness Directives; Gulfstream

Model G–1159, G–1159A, G–1159B, G–

IV, and G–V Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This amendment corrects and

clarifies information in an existing

airworthiness directive (AD), applicable

to certain Gulfstream Model G–1159, G–

1159A, G–1159B, G–IV, and G–V series

airplanes, that currently requires an

inspection to determine if certain door

control valves of the landing gear are

installed, and modification of the valve,

if necessary. The actions specified in

that AD are intended to prevent loss of

hydraulic system fluid due to failure of

the door control valve of the landing

gear, which could require the flight

crew to use alternate gear extension

procedures (landing gear blow down)

for landing of all models. This

amendment corrects the requirements of

the current AD by specifying

appropriate alert customer bulletins for

certain airplane models, and clarifying

the compliance time for the

modification of the door control valve of

the landing gear. This amendment is

prompted by operators’ comments on

the existing AD.

DATES: Effective May 10, 2001.

The incorporation by reference of

certain publications listed in the

regulations was approved previously by

the Director of the Federal Register as of

May 10, 2001 (66 FR 20734, April 25,

2001).

FOR FURTHER INFORMATION CONTACT:

Frank Mokry, Aerospace Engineer,

Systems and Flight Test Branch, ACE–

116A, FAA, Atlanta Aircraft

Certification Office, One Crown Center,

1895 Phoenix Boulevard, suite 450,

Atlanta, Georgia 30349; telephone (770)

703–6066; fax (770) 703–6097.

SUPPLEMENTARY INFORMATION: On April

16, 2001, the Federal Aviation

Administration (FAA) issued

Airworthiness Directive (AD) 2001–08–

13, amendment 39–12191 (66 FR 20734,

April 25, 2001), which applies to certain

Gulfstream Model G–1159, G–1159A,

G–1159B, G–IV, and G–V series

airplanes. That AD requires inspection

and modification of certain door control

valves of the nose landing gear and the

main landing gear. The actions required

by that AD are intended to prevent loss

of hydraulic system fluid due to failure

of the door control valve of the landing

gear, which could require the flight

crew to use alternate gear extension

procedures (landing gear blow down)

for landing of all models.

Need for the Correction and

Clarification

Since the issuance of that AD, the

FAA has received information that

requires certain corrections and

clarifications for that AD.

In indicating which Gulfstream alert

customer bulletin to use in

accomplishing the required actions for

each of the five Gulfstream airplane

models affected, the FAA inadvertently

reversed the bulletins indicated for the

G–1159, G–1159B, and G–1159A

Gulfstream models. That information

also was included in the applicability

section in the table entitled ‘‘Gulfstream

Airplane Models and Alert Customer

Bulletins (ACB)’’ and in paragraph (b) of

AD 2001–08–13. This document

corrects the references to the

appropriate alert customer bulletins,

and will ensure that the appropriate

Gulfstream bulletin is used to

accomplish the actions required by this

AD for each of the five Gulfstream

models to which it applies.

Additionally, this document also

corrects and clarifies the compliance

time specified for the actions specified

in paragraph (b) of the AD. The FAA

inadvertently specified the compliance

times for paragraphs (b)(1) and (b)(2) of

the AD as ‘‘* * * after the effective date

of this AD.’’ We intended that the

requirements of paragraph (b) of that AD

should read ‘‘* * * after the date of

inspection accomplished per the

requirements of paragraph (a) of this

AD.’’ Correction of that wording permits

a somewhat extended compliance time

for the operators to accomplish the

requirements of paragraph (b) of this

AD. Therefore, this correction is a

relieving requirement for operators and

necessitates no additional work or cost

burdens.

Correction of the Publication

This document corrects an error,

clarifies certain requirements, and

correctly adds the AD as an amendment

to section 39.13 of the Federal Aviation

Regulations (14 CFR 39.13).

The AD is being reprinted in its

entirety for the convenience of affected

operators. The effective date of the AD

remains May 10, 2001.

Since this action only clarifies a

current requirement, it has no adverse

economic impact and imposes no

additional burden on any person.

Therefore, notice and public procedures

hereon are unnecessary.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Correction

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 [Corrected]

2. Section 39.13 is amended by

correctly adding a new airworthiness

directive, to read as follows:

2001–08–13 Gulfstream Aerospace

Corporation: Amendment 39–12191.

Docket 2001–NM–83–AD.

Applicability: Model G–1159, G–1159A, G–

1159B, G–IV, and G–V series airplanes, as

specified in the Gulfstream Alert Customer

Bulletins listed in the following table;

certificated in any category: