40812 Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations

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 failure of the FSOV’s to close,

which would result in failure of the engine

fire shut-off system, and consequently

inability to extinguish an engine fire,

accomplish the following:

(a) Within 500 flight hours after the

effective date of this AD, perform a one-time

operational test of the 4 fire shut-off valves

(FSOV’s) on the airplane, in accordance with

Airbus All Operator Telex (AOT) 29–22,

dated November 24, 1997. If any FSOV fails

the test, prior to further flight, replace the

failed FSOV or actuator, as applicable, with

a new or serviceable FSOV or actuator, as

applicable, in accordance with AOT 29–22.

(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,

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.

(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 Airbus All Operator Telex (AOT) 29–22,

dated November 24, 1997. 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 97–384–

241(B)R1, dated January 14, 1998.

(e) 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. 98–20432 Filed 7–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–42–AD; Amendment

39–10680; AD 98–16–05]

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

inspections of the areas behind the scuff

plates below the passenger/crew doors

and bulk cargo door to detect cracks and

corrosion, and repair, if necessary. This

amendment also requires inspections to

detect cracking of the holes of the corner

doublers, the fail-safe ring, and the door

frames of the door structures; and

repair, if necessary. In addition, this

amendment provides for optional

terminating action for certain

inspections. This amendment is

prompted by reports indicating that

corrosion was found behind the scuff

plates at exit and cargo doors, and

fatigue cracks originated from certain

fastener holes located in adjacent

structure. The actions specified by this

AD are intended to detect and correct

such corrosion and fatigue cracking,

which could result in reduced structural

integrity of the door surroundings.

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 all Airbus Model

A300–600 series airplanes was

published in the Federal Register on

January 29, 1997 (62 FR 4211). That

action proposed to require inspections

of the lower door surrounding structure

to detect cracks and corrosion, and

repair, if necessary. That action also

proposed to require inspections to

detect cracking of the holes of the corner

doublers, the fail-safe ring, and the door

frames of the door structures; and

repair, if necessary. In addition, that

action proposed to provide for optional

terminating action for certain

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.

Clarification of Terminology

One commenter expresses no

objection to the proposed rule, but

requests that certain terminology in the

proposed AD be changed for the sake of

clarity. The commenter states that the

title is not complete, since it refers only

to inspections of the lower door

structure, while inspection of the upper

door corners is also required. The FAA

concurs. The FAA infers that the

commenter is referring to the Summary

section of the proposed AD, which

states that ‘‘this proposal would require

inspections of the lower door

surrounding structure.’’ However, in all

other sections of the proposed AD, the

area to be inspected is described as ‘‘the

areas behind the scuff plates below the

passenger/crew doors and bulk cargo

door,’’ in accordance with procedures

described in Airbus Service Bulletin

A300–53–6011, Revision 3, dated

February 4, 1991. To avoid confusion

regarding the area to be inspected for

cracks and corrosion, the Summary

section of the final rule has been

changed to correspond to the

terminology used elsewhere throughout

the AD.

The same commenter requests that

paragraphs (b) and (d) of the proposed

AD be changed to refer to the ‘‘fail-safe

ring and corner strap,’’ rather than the

existing terminology of ‘‘fail-safe ring

and corner doubler.’’ The commenter

states that the term ‘‘corner strap’’ is

used in Airbus Service Bulletin A300–

53–6022, dated February 4, 1991, and in

other maintenance documents, rather

than ‘‘corner doubler.’’ The FAA does
Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations 40813

not concur. The FAA has verified that

the referenced service bulletin uses the

term ‘‘corner doubler’’ to identify the

affected part. Therefore, the usage of

this terminology has been retained in

the final rule.

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 with the change

described previously. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

The FAA estimates that 35 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 700

work hours per airplane to accomplish

the required inspections (including

access and close-up), and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the required AD on U.S. operators is

estimated to be $1,470,000, or $42,000

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.

Should an operator elect to

accomplish the optional terminating

action that is provided by this AD

action, it will take approximately 147

work hours to accomplish it, at an

average labor rate of $60 per work hour.

The cost of required parts will be

approximately $5,581 per airplane.

Based on these figures, the cost impact

of the optional terminating action will

be $14,401 per airplane.

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:

98–16–05 Airbus: Amendment 39–10680.

Docket 96–NM–42–AD.

Applicability: All Model A300–600 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 (i) 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 corrosion behind the

scuff plates at exit and cargo doors, and

fatigue cracking in certain fastener holes

located in adjacent structure, which could

result in reduced structural integrity of the

door surroundings, accomplish the following:

(a) Perform an initial inspection of the

areas behind the scuff plates below the

passenger/crew doors and bulk cargo door to

detect cracks and corrosion, in accordance

with Airbus Service Bulletin A300–53–6011,

Revision 3, dated February 4, 1991; at the

time specified in paragraph (a)(1), (a)(2), or

(a)(3) of this AD. If any crack or corrosion is

found during this inspection, prior to further

flight, repair in accordance with the service

bulletin. Accomplishment of this inspection

is not required for the mid and aft passenger/

crew doors if a steel doubler that covers the

entire inspection area is installed.

(1) For airplanes on which Modification

5382S6526 (for forward doors) and

Modification 5382D4741 (for all other doors)

have been accomplished prior to delivery of

the airplane: Perform the initial inspection

within 9 years since date of manufacture, or

within 1 year after the effective date of this

AD, whichever occurs later.

(2) For airplanes on which Modification

5382S6526 (for forward doors) and

Modification 5382D4741 (for all other doors)

have not been accomplished; and on which

the procedures described in Airbus Service

Information Letter (SIL) A300–53–033,

Revision 2 (for all doors), dated November

23, 1984, have been accomplished: Perform

the initial inspection within 5 years after

accomplishment of the procedures described

in the SIL, or within 1 year after the effective

date of this AD, whichever occurs later.

(3) For airplanes on which Modification

5382S6526 (for forward doors), Modification

5382D4741 (for all other doors), and the

procedures described in Airbus SIL A300–

53–033, Revision 2, dated November 23,

1984, have not been accomplished:

Perform the initial inspection within 4

years since date of manufacture, or within 1

year after the effective date of this AD,

whichever occurs later.

(b) Perform repetitive inspections of the

areas behind the scuff plates below the

passenger/crew doors and bulk cargo door to

detect cracks and corrosion, in accordance

with Airbus Service Bulletin A300–53–6022,

dated February 4, 1991; at the applicable

times specified in paragraphs (b)(1) and (b)(2)

of this AD. Accomplishment of these

inspections is not required for the mid and

aft passenger/crew doors if a steel doubler

that covers the entire inspection area is

installed.

(1) For the forward and mid passenger/

crew doors, the bulk cargo door, and the aft

passenger/crew doors, except the upper and

lower edges of the fail-safe ring and the

upper edges of the corner doubler: Perform

the first inspection within 5 years after

accomplishing the inspection required by

paragraph (a) of this AD; and repeat the

inspection thereafter at intervals not to

exceed 5 years.

(2) 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: Perform the first inspection within 5

years or 6,000 landings after accomplishing

the inspection required by paragraph (a) of

this AD, whichever occurs first; and repeat

the inspection thereafter at intervals not to

exceed 5 years or 6,000 landings, whichever

occurs first.

(c) If any crack 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
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.