40816 Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations

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 corrosion or plating

cracks of the pin assemblies in the front

trunnion support of the main landing gear

(MLG), which could cause these assemblies

to break and result in collapse of the MLG,

accomplish the following:

(a) Perform a close visual inspection to

detect corrosion or plating cracks of each

4330M Steel pin assembly in the forward

trunnion support of the MLG, in accordance

with Boeing Alert Service Bulletin 767–

57A0047, Revision 1, dated May 9, 1996, at

the later of the times specified in paragraphs

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

(1) Within 4 years since date of

manufacture of the airplane, or 4 years since

the last overhaul of the MLG. Or

(2) Within 18 months after the effective

date of this AD.

(b) If no corrosion or crack is detected,

repeat the close visual inspection thereafter

at intervals not to exceed 48 months.

(c) If any corrosion or crack is detected,

prior to further flight, replace it with a new

pin assembly made from 15–5PH CRES with

Class 3 chrome plating, in accordance with

Boeing Alert Service Bulletin 767–57A0047,

Revision 1, dated May 9, 1996.

(d) Accomplishment of replacement of a

4330M Steel pin assembly with a new pin

assembly made from 15–5PH CRES with

Class 3 chrome plating, in accordance with

Boeing Alert Service Bulletin 767–57A0047,

Revision 1, dated May 9, 1996, constitutes

terminating action for the inspections

required by this AD for that pin location.

Note 2: Replacement of a 4330M Steel pin

assembly with a new pin assembly made

from 15–5PH CRES with Class 3 chrome

plating prior to the effective date of this AD,

in accordance with Boeing Service Bulletin

767–57A0047, dated January 19, 1995, is

considered an acceptable method of

compliance with paragraph (d) of this AD for

that pin location.

(e) 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

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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(f) 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.

(g) The inspections and replacement shall

be done in accordance with Boeing Alert

Service Bulletin 767–57A0047, Revision 1,

dated May 9, 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.

(h) This amendment becomes effective on

September 4, 1998.

Issued in Renton, Washington, on July 24,

1998.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20340 Filed 7–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–116–AD; Amendment

39–10687; AD 98–16–11]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A310, and A300–600 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A300, A310, and A300–600 series

airplanes, that requires repetitive

detailed visual inspections to detect

cracks in the pylon thrust and sideload

fitting of the wing, and replacement of

any cracked pylon thrust and sideload

fitting with a new fitting. This

amendment is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by this AD are intended to

detect and correct cracks in the pylon

thrust and sideload fitting of the wing,

which could result in reduced structural

integrity of the airplane.

DATES: Effective September 4, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of September

4, 1998.

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) to

include an airworthiness directive (AD)

that is applicable to certain Airbus

Model A300, A310, and A300–600

series airplanes was published in the

Federal Register on May 28, 1998 (63

FR 29153). That action proposed to

require repetitive detailed visual

inspections to detect cracks in the pylon

thrust and sideload fitting of the wing,

and replacement of any cracked pylon

thrust and sideload fitting with a new

fitting.

Comments

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

The FAA estimates that 126 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 3

work hours per airplane to accomplish

the required inspection, 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 $22,680, or $180 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.

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
Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations 40817

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:

98–16–11 Airbus Industrie: Amendment

39–10687. Docket 98–NM–116–AD.

Applicability: Model A300 series airplanes,

as listed in Airbus Service Bulletin A300–57–

0232, Revision 01, dated January 12, 1998;

Model A310 series airplanes, as listed in

Airbus Service Bulletin A310–57–2075,

Revision 01, dated January 12, 1998; and

Model A300–600 series airplanes, as listed in

Airbus Service Bulletin A300–57–6079,

Revision 02, dated January 12, 1998;

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 as indicated, unless

accomplished previously.

To detect and correct cracks in the pylon

thrust and sideload fitting of the wing, which

could result in reduced structural integrity of

the airplane, accomplish the following:

(a) Prior to the accumulation of 2,800 total

flight cycles, or within 18 months after the

effective date of this AD, whichever occurs

later, perform a detailed visual inspection to

detect cracks in the pylon thrust and sideload

fitting of the wing, in accordance with Airbus

Service Bulletin A300–57–0232, Revision 01

(for Model A300 series airplanes); A310–57–

2075, Revision 01 (for Model A310 series

airplanes); or A300–57–6079, Revision 02

(for Model A300–600 series airplanes); all

dated January 12, 1998; as applicable. Repeat

the detailed visual inspection thereafter at

intervals not to exceed 2,800 flight cycles.

(b) If any crack is detected during any

inspection required by paragraph (a), prior to

further flight, replace the pylon thrust and

sideload fitting with a new fitting in

accordance with Airbus Service Bulletin

A300–57–0232, Revision 01 (for Model A300

series airplanes); A310–57–2075, Revision 01

(for Model A310 series airplanes); or A300–

57–6079, Revision 02 (for Model A300–600

series airplanes); all dated January 12, 1998;

as applicable. Thereafter, continue the

inspections in accordance with the

requirements of paragraph (a) of this AD.

(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,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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 inspections and replacement shall

be done in accordance with Airbus Service

Bulletin A300–57–0232, Revision 01, dated

January 12, 1998; Airbus Service Bulletin

A310–57–2075, Revision 01, dated January

12, 1998; or Airbus Service Bulletin A300–

57–6079, Revision 02, dated January 12,

1998; 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 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 3: The subject of this AD is addressed

in French airworthiness directive 97–358–

232(B), dated November 19, 1997.

(f) This amendment becomes effective on

September 4, 1998.

Issued in Renton, Washington, on July 24,

1998.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20434 Filed 7–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–90–AD; Amendment

39–10686; AD 98–16–10]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Dornier Model

328–100 series airplanes, that requires

revising the Airplane Flight Manual

(AFM) to require use of the electrical

fuel pump for take-off and landing and

performance of an operational check of

the electrical fuel pump following

landing. This amendment also requires

replacement of the jet booster pumps

with new or modified jet booster

pumps, which terminates the

requirement for the AFM revision. This

amendment is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by this AD are intended to

prevent failure of the jet booster pumps,

which could result in reduced engine

thrust during take-off or landing, and

consequent increased risk of impact

with terrain.

DATES: Effective September 4, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of September

4, 1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from FAIRCHILD DORNIER, DORNIER