Federal Register / Vol. 63, No. 142 / Friday, July 24, 1998 / Proposed Rules 39769

(e) Within 20 years since date of

manufacture, or within 24 months after the

effective date of this AD, whichever occurs

later: Replace the silver-plated copper FQIS

wiring of the center fuel tank with new

nickel-plated copper FQIS wiring, in

accordance with 747 Maintenance Manual,

chapters 28–11–00, 28–41–00, 28–41–01, 28–

41–02, and 28–41–09.

(f) For airplanes having line positions 1

through 971 inclusive: Within 24 months

after the effective date of this AD, install a

flame arrestor in the inlet line of the

electrical motor-operated scavenge pump of

the center fuel tank, in accordance with

Boeing Alert Service Bulletin 747–28A2210,

dated May 14, 1998.

(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

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.

(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.

Issued in Renton, Washington, on July 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–19460 Filed 7–23–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–106–AD]

RIN 2120–AA64

Airworthiness Directives; Short

Brothers Model SD3–60 and SD3–60

SHERPA Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Supplemental notice of

proposed rulemaking; reopening of

comment period.

SUMMARY: This document revises an

earlier proposed airworthiness directive

(AD), applicable to all Short Brothers

Model SD3–60 series airplanes, that

would have required repetitive

inspections to detect corrosion and/or

wear of the top and bottom shear decks

of the left and right stub wings in the

area of the forward pintle pin of the

main landing gear (MLG), and repair, if

necessary. That proposal was prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. This new

action revises the proposed rule by

expanding the applicability to include

an additional airplane model. The

actions specified by this new proposed

AD are intended to detect and correct

corrosion and/or wear of the top and

bottom shear decks of the left and right

stub wings in the area of the forward

pintle pin of the MLG, which could

result in failure of the MLG to extend or

retract.

DATES: Comments must be received by

August 18, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

106–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Short Brothers, Airworthiness &

Engineering Quality, P. O. Box 241,

Airport Road, Belfast BT3 9DZ,

Northern Ireland. This information may

be examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

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:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97-NM–106-AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

97–NM–106–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to add an airworthiness

directive (AD), applicable to all Short

Brothers Model SD3–60 series airplanes,

was published as a notice of proposed

rulemaking (NPRM) in the Federal

Register on October 6, 1997 (62 FR

52053). That NPRM would have

required repetitive inspections to detect

corrosion and/or wear of the top and

bottom shear decks of the left and right

stub wings in the area of the forward

pintle pin of the main landing gear

(MLG), and repair, if necessary. That

NPRM was prompted by reports of

corrosion and/or wear of the top and

bottom shear decks of the left and right

stub wings in the area of the forward

pintle pin of the MLG. Such corrosion

or wear of the top and bottom shear

decks of the left and right stub wings in

the area of the forward pintle pin of the

MLG, if not corrected, could result in

failure of the MLG to extend or retract.

Actions Since Issuance of Previous

Proposal

Since the issuance of that NPRM, the

Civil Aviation Authority (CAA), which

is the airworthiness authority for the

United Kingdom, notified the FAA that

the unsafe condition described in the

original NPRM also may exist on all

Short Brothers Model SD3–60 SHERPA

series airplanes. The shear decks of the

stub wings on Model SD3–60 SHERPA

series airplanes are similar in design to

those on Model SD3–60 series airplanes;

therefore, both models are subject to the

same unsafe condition. The FAA has

revised the applicability of this
39770 Federal Register / Vol. 63, No. 142 / Friday, July 24, 1998 / Proposed Rules

supplemental NPRM to add Model SD3–

60 SHERPA series airplanes.

New Service Information

Short Brothers has issued Service

Bulletin SD3–60 SHERPA–53–3, dated

November 4, 1997, which describes

procedures for repetitive inspections to

detect corrosion and/or wear of the top

and bottom shear decks of the left and

right stub wings in the area of the

forward pintle pin of the MLG, and

repair, if necessary. For airplanes on

which certain depths of corrosion or

wear is detected, the service bulletin

describes procedures for a visual

inspection to detect any discrepancy of

the pintle pin and sleeve. The CAA

classified this service bulletin as

mandatory and issued British

airworthiness directive 005–11–97 in

order to assure the continued

airworthiness of these airplanes in the

United Kingdom.

The FAA has revised this

supplemental NPRM to reference this

service bulletin as the appropriate

source of service information for

accomplishment of the actions proposed

by this AD for Model SD3–60 SHERPA

series airplanes.

Explanation of Change Made to NPRM

In the original NPRM, the FAA

inadvertently omitted a paragraph

requiring operators to repeat the

inspection for corrosion of the top and

bottom shear decks of the left and right

stub wings at intervals not to exceed 6

months even if no corrosion, wear, or

discrepancy of the measurement of the

holes for the retaining pin of the pintle

pin is found. Accordingly, the FAA has

included this requirement in paragraph

(a)(1) of this supplemental NPRM.

Conclusion

Since these changes expand the scope

of the originally proposed rule, the FAA

has determined that it is necessary to

reopen the comment period to provide

additional opportunity for public

comment.

Cost Impact

The FAA estimates that 58 Model

SD3–60 series airplanes and 28 Model

SD3–60 SHERPA series airplanes of U.S.

registry would be affected by this

proposed AD, that it would take

approximately 13 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $67,080, or $780 per

airplane, per inspection cycle.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed 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 proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Short Brothers PLC: Docket 97-NM–106-AD.

Applicability: All Model SD3–60 and SD3–

60 SHERPA 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 (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 corrosion and/or

wear of the top and bottom shear decks of the

left and right stub wings in the area of the

forward pintle pin of the main landing gear

(MLG), which could result in failure of the

MLG to extend or retract, accomplish the

following:

(a) Within 90 days after the effective date

of this AD, conduct an inspection for

corrosion of the top and bottom shear decks

of the left and right stub wings in the area

of the forward pintle pin of the MLG, and

measure the retaining pin holes of the pintle

pin for wear; in accordance with Part A. of

the Accomplishment Instructions of Short

Brothers Service Bulletin SD360–53–42,

dated September 1996 (for Model SD3–60

series airplanes), or Short Brothers Service

Bulletin SD3–60 SHERPA–53–3, dated

November 4, 1997 (for Model SD3–60

SHERPA series airplanes), as applicable.

(1) If no corrosion, wear, or discrepancy of

the measurement of the holes for the

retaining pin of the pintle pin is found,

repeat the inspection required by paragraph

(a) of this AD thereafter at intervals not to

exceed 6 months.

(2) If any corrosion, wear, or measurement

of the holes for the retaining pin of the pintle

pin is found that is within the limits

specified in Part A. of the Accomplishment

Instructions of the applicable service

bulletin, prior to further flight, repair the

discrepancy in accordance with the

applicable service bulletin. Thereafter, repeat

the inspection required by paragraph (a) of

this AD at intervals not to exceed 6 months.

(3) If any corrosion, wear, or measurement

of the holes for the retaining pin of the pintle

pin is found that is beyond the limits

specified in Part A. of the Accomplishment

Instructions of the applicable service

bulletin, prior to further flight, perform the

actions required by paragraph (a)(3)(i) and

(a)(3)(ii) of this AD.

(i) Remove the corrosion and install

bushings on the upper and lower shear webs

in the retaining pin holes for the pintle pin

in accordance with Part B. (left MLG) and/

or Part C. (right MLG), as applicable, of the

Accomplishment Instructions of the

applicable service bulletin.

(ii) Perform a visual inspection of the

pintle pin and the sleeve for any discrepancy,

in accordance with Part B. and/or Part C., as

applicable, of the Accomplishment

Instructions of the applicable service

bulletin.
Federal Register / Vol. 63, No. 142 / Friday, July 24, 1998 / Proposed Rules 39771

(A) If no discrepancy is detected, the pintle

pin and the sleeve of the pintle pin may be

returned to service.

(B) If any discrepancy of the pintle pin and

sleeve is detected, prior to further flight,

repair the pintle pin and sleeve in

accordance with a method approved by the

Manager, International Branch, ANM–116,

FAA, Transport Airplane Directorate.

(b) Removal of corrosion and installation of

bushings in accordance with Part B. and/or

Part C., as applicable, of the Accomplishment

Instructions of Short Brothers Service

Bulletin SD360–53–42, dated September

1996 (for Model SD3–60 series airplanes), or

Short Brothers Service Bulletin SD3–60

SHERPA–53–3, dated November 4, 1997 (for

Model SD3–60 SHERPA series airplanes), as

applicable, constitutes terminating action for

the repetitive inspection requirements 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. 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 §§ 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.

Note 3: The subject of this AD is addressed

in British airworthiness directives 005–09–96

and 005–11–97.

Issued in Renton, Washington, on July 20,

1998.

S. R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–19778 Filed 7–23–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–107–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310, A300–600, and A320 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to certain

Airbus Model A310, A300–600, and

A320 series airplanes, that currently

requires inspections to verify proper

installation of the grill over the air

extraction duct of the lavatory and to

detect blockages in the air extraction

duct of the lavatory, and correction of

any discrepancies. This action would

add a requirement for modification of

the grill of the air extraction duct,

which, when accomplished, would

terminate the repetitive inspections.

This action also would expand the

applicability of the existing AD to

include additional airplanes. This

proposal is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by the proposed AD are

intended to prevent obstructions in the

air extraction system of the lavatory,

which may result in the failure of the

smoke detection system to detect smoke

in the lavatories.

DATES: Comments must be received by

August 24, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

107–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

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:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97–NM–107–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

97–NM–107–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On February 17, 1995, the FAA issued

AD 95–04–12, amendment 39–9164 (60

FR 11619, March 2, 1995), applicable to

certain Airbus Model A310, A300–600,

and A320 series airplanes, to require

inspections to verify proper installation

of the grill over the air extraction duct

of the lavatory and to detect blockages

in the air extraction duct of the lavatory,

and correction of any discrepancies.

That action was prompted by reports of

obstructions in the air extraction system

of the lavatories. The requirements of

that AD are intended to prevent

obstructions in the air extraction system

of the lavatory, which may result in the

failure of the smoke detection system to

detect smoke in the lavatories.

Actions Since Issuance of Previous Rule

Since the issuance of that AD, the

Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC), which is the airworthiness

authority for France, notified the FAA

that it has received several additional

reports of incorrectly installed grill

hoods of the air extraction system of the

lavatory on certain Airbus Model A310,

A300–600, and A320 series airplanes.

This condition, if not corrected, could

result in obstructions in the air

extraction system, and consequent

failure of the smoke detection system to

detect smoke in the lavatories.