40814 Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations

applicable times specified in paragraphs

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

(d) If corrosion is found during any

inspection required by paragraph (b) of this

AD, prior to further flight, repair in

accordance with Airbus Service Bulletin

A300–53–6022, dated February 4, 1991.

Thereafter, perform the repetitive inspections

required by paragraph (b) of this AD at the

applicable times specified in paragraphs

(d)(1) or (d)(2) of this AD.

(1) For the upper and lower edges of the

fail-safe ring and the upper edges of the

corner doubler of the aft passenger/crew

doors, and for the mid passenger/crew door:

Inspect at intervals not to exceed 5 years or

5,000 landings, whichever occurs first.

(2) For the forward passenger/crew doors

and bulk cargo doors: Inspect at intervals not

to exceed 5 years.

(e) Perform an inspection to detect cracking

of the holes of the corner doublers, the failsafe ring, and the door frames of the left- and

right-hand forward, mid, and aft passenger/

crew door structures, in accordance with

Airbus Service Bulletin A300–53–6018,

Revision 1, dated April 29, 1992, and at the

applicable time specified in paragraph (e)(1),

(e)(2), (e)(3), or (e)(4) of this AD.

(1) For the upper corners of the forward

doors: Inspect prior to the accumulation of

20,000 total landings, or within 2,000

landings after the effective date of this AD,

whichever occurs later.

(2) For the lower corners of the forward

doors: Inspect prior to the accumulation of

20,000 total landings, or within 4,000

landings after the effective date of this AD,

whichever occurs later.

(3) For the upper and lower corners of the

mid doors: Inspect prior to the accumulation

of 20,000 total landings, or within 2,000

landings after the effective date of this AD,

whichever occurs later.

(4) For the upper and lower corners of the

aft doors, and for the parts underneath the

corners of the upper door frames: Inspect

prior to the accumulation of 20,000 total

landings, or within 4,000 landings after the

effective date of this AD, whichever occurs

later.

(f) Repeat the inspections required by

paragraph (e) of this AD at the applicable

times specified in paragraphs (f)(1), (f)(2),

(f)(3), (f)(4), and (f)(5).

(1) For the upper corners of the forward

doors: Inspect at intervals not to exceed 6,000

landings.

(2) For the lower corners of the forward

doors: Inspect at intervals not to exceed

10,000 landings.

(3) For the upper and lower corners of the

mid and aft doors on which an inspection

required by paragraph (e) of this AD was

accomplished using a Roto test technique:

Inspect at intervals not to exceed 8,000

landings.

(4) For the upper and lower corners of the

mid and aft doors on which an inspection

required by paragraph (e) of this AD was

accomplished using an X-ray technique:

Inspect at intervals not to exceed 3,500

landings.

(5) For the areas around the fasteners in the

vicinity of stringer 12 on the upper door

frames of the aft doors on which an

inspection required by paragraph (e) of this

AD was accomplished using a visual

technique: Inspect at intervals not to exceed

6,900 landings.

(g) If any crack is found during any

inspection required by paragraph (e) or (f) of

this AD: Prior to further flight, accomplish

the requirement of paragraph (g)(1) or (g)(2)

of this AD, as applicable.

(1) If any crack is found, and the crack can

be eliminated using the method specified in

Airbus Service Bulletin A300–53–6018,

Revision 1, dated April 29, 1992: Prior to

further flight, repair the crack in accordance

with that service bulletin.

(2) If any crack is found, and the crack

cannot be eliminated using the method

specified in Airbus Service Bulletin A300–

53–6018, Revision 1, dated April 29, 1992:

Prior to further flight, repair the crack in

accordance with a method approved by the

Manager, International Branch, ANM–116,

FAA, Transport Airplane Directorate.

(h) Modification of the passenger/crew

door frames in accordance with Airbus

Service Bulletin A300–53–6002, Revision 3,

dated February 22, 1992, constitutes

terminating action for the repetitive

inspections required by paragraph (f) of this

AD.

(i) 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.

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.

(j) 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.

(k) Except as provided by paragraph (g)(2)

of this AD, the actions shall be done in

accordance with the following Airbus service

bulletins, which contain the specified list of

effective pages:

Service bulletin referenced and date Page number shown on page Revision level shown

on page Date shown on page

A300–53–6022, February 4, 1991 ............................................. 1–15 ......................................... Original ...................... February 4, 1991.

A300–53–6002, Revision 3, February 22, 1992 ........................ 1–2, 56, 67–68 ........................ 3 ................................ February 22, 1992.

3–26, 31–55, 57–66 ................ 1 ................................ February 4, 1991.

27–30 ....................................... 2 ................................ May 6, 1991.

A300–53–6011, Revision 3, February 4, 1991 .......................... 1–17 ......................................... 3 ................................ February 4, 1991.

A300–53–6018, Revision 1, April 29, 1992 ............................... 1, 3–4, 9–14, 17, 24, 31–34,

36, 50.

1 ................................ April 29, 1992.

2, 5–8, 15–16, 18–23, 25–30,

35, 37–49, 51–65.

Original ...................... February 4, 1991.

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 91–132–

124(B), dated June 26, 1991, as amended by

a Correction, dated August 21, 1991.

(l) This amendment becomes effective on

September 4, 1998.

Issued in Renton, Washington, on July 24,

1998.

D.L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20337 Filed 7–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–52–AD; Amendment

39–10683; AD 98–16–07]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 767 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.
Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations 40815

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 767

series airplanes, that requires repetitive

inspections to detect corrosion or

plating cracks of the pin assemblies in

the forward trunnion support of the

main landing gear (MLG), and

replacement of the pin assembly with a

new assembly, if necessary. Such

replacement, if accomplished,

constitutes terminating action for the

repetitive inspections. This amendment

is prompted by reports indicating that

these pin assemblies were found to have

corroded as a result of plating cracks.

The actions specified by this AD are

intended to detect and correct such

corrosion and plating cracks, which

could cause breakage of these

assemblies, and consequent collapse of

the MLG.

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 Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207. 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:

James G. Rehrl, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington; telephone (425) 227–2783;

fax (425) 227–1181.

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 Boeing

Model 767 series airplanes was

published in the Federal Register on

July 22, 1997 (62 FR 39195). That action

proposed to require repetitive

inspections to detect corrosion or

plating cracks of the pin assemblies in

the forward trunnion support of the

main landing gear (MLG), and

replacement of the pin assembly with a

new assembly, if necessary. Such

replacement, if accomplished, would

constitute terminating action for the

repetitive inspections.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Two commenters support the

proposed rule.

One commenter generally supports

the proposed rule, but expresses

concern regarding the planned

compliance time in the proposed AD for

installation of new fuse pins. The

commenter notes that it currently plans

to install new fuse pins on its entire

fleet of airplanes by April 2003,

concurrent with scheduled gear

changes. If the proposed AD requires

installation of fuse pins in a shorter time

period, additional maintenance costs

will be incurred by this operator.

Although no specific request is made

by this commenter, the FAA infers that

the commenter believes the installation

of improved fuse pins to be a required

action in the proposed AD. However,

the proposed AD does not require

installation of the improved fuse pins

unless corrosion or cracking is detected,

although such installation is provided

as an optional terminating action for the

repetitive inspection requirements of

this AD. In light of this, the FAA has

determined that no change to the final

rule is necessary.

Conclusion

After careful review of the available

data, including the comments 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 562 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 65 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

$588,900, or $3,900 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

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:

98–16–07 Boeing: Amendment 39–10683.

Docket 97–NM–52–AD.

Applicability: Model 767 series airplanes

having line positions 1 through 562

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

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 (e) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by
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