Airworthiness directives: Pratt & Whitney Correction,
[Federal Register: October 18, 2006 (Volume 71, Number 201)]
[Rules and Regulations]
[Page 61395-61399]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18oc06-6]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA-2006-25809; Directorate Identifier 2001-NE-30-AD; Amendment 39-14791; AD 2006-17-07R1]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney JT8D-1, -1A, -1B, -7, - 7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, - 217A, -217C, and -219 Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT).
ACTION: Final rule; correction.
SUMMARY: The FAA is revising an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 turbofan engines. That AD currently requires either replacing high pressure compressor (HPC) front hubs and HPC disks that have operated at any time with PWA 110-21 coating and that operated in certain engine models, or, visually inspecting and fluorescent penetrant inspecting (FMPI) for cracking of those parts and re-plating them if they pass inspection. This AD requires the same actions, but makes necessary corrections to inadvertent reference errors and omissions found in AD 2006-17-07, and relaxes some of the compliance times in Table 5. This AD results from our finding reference errors and omissions in AD 2006- 17-07, from determining that the AD as drafted imposed an unnecessary burden on operators if they have to immediately remove engines, and from requests to clarify compliance paragraphs. We are issuing this AD to prevent a rupture of an HPC front hub or an HPC disk that could result in an uncontained engine failure and damage to the airplane.
DATES: This AD becomes effective November 2, 2006. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of October 4, 2006 (71 FR 51459, August 30, 2006).
ADDRESSES: You can get the service information identified in this AD from Pratt & Whitney, 400 Main St., East Hartford, CT 06108, telephone (860) 565-7700; fax (860) 565-1605.
You may examine the AD docket on the Internet at http://dms.dot.gov
or in Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Keith Lardie, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238- 7189; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: On August 21, 2006, the FAA issued AD 2006- 17-07, Amendment 39-14728 (71 FR 51459, August 30, 2006). That AD requires either replacing HPC front hubs and HPC disks that have operated at any time with PWA 110-21 coating and that operated in certain engine models, or, visually inspecting and FMPI for cracking of those parts and re-plating them if they pass inspection. That AD was the result of an investigation by PW, which concluded that any HPC front hub or HPC disk coated with PWA 110-21 that ever operated on JT8D-15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and - 219 turbofan engines, could crack before reaching their published life limit. That condition, if not corrected, could result in an uncontained engine failure and damage to the airplane.
Examining the AD Docket
You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647-5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them.
Actions Since AD 2006-17-07 Was Issued
After we issued AD 2006-17-07, we found reference errors and omissions. These errors and omissions could affect your ability to comply with the AD. The following errors and omissions were discovered. We made the associated corrections:
In the third column of Table 1 of this AD, we omitted ``- 17A'' in two places. We added the missing ``-17A'' from AD 2006-17-07 in both places.
The third column of Table 4 and Table 5 reads ``Paragraph (h)(3) of this AD''. Paragraph (h)(3) does not exist. We corrected it to read ``Paragraph (j) of this AD.''
We also determined that based on the compliance times in Table 5 of AD 2006-17-07, some operators might have to immediately remove their engines from service. If so, we concluded that those immediate removals might impose an unanticipated undue burden. Table 5 of AD 2006-17-07, appears below.
[[Page 61396]]
Table 5 of AD 2006-17-07--HPC Front Hub Inspection Schedule--Hubs Coated With Nickel-Cadmium
Also inspect 7th Inspect before stage HPC disks
HPC front hub CSN on the additional CIS or and 9th stage-
effective date of this AD CSN, whichever through-12th stage occurs first HPC disks using:
(i) 19,000 or more.............. 500 CIS or 20,000 Paragraph (h)(3) CSN.
of this AD. (ii) 17,000 or more, but fewer 1,000 CIS or
Paragraph (h)(3) than 19,000.
19,500 CSN.
of this AD. (iii) 9,000 or more, but fewer 18,000 CSN........ Paragraph (h)(3) than 17,000, that have not been
of this AD. inspected. (iv) 9,000 or more, but fewer 15,500 CSN........ Paragraph (h)(3) than 17,000, that were
of this AD. inspected before accumulating 9,000 CSN.
Therefore, we changed Table 5 to reflect relaxed compliance requirements in item (iii), and we changed the compliance requirements in item (iv). With the addition of the ``-17A'' noted previously, and the changed compliance requirements that relax compliance time, Table 5 now reads as follows:
(Changed) Table 5.--HPC Front Hub Inspection Schedule--Hubs Coated With Nickel-Cadmium
Also inspect 7th Inspect before stage HPC disks
HPC front hub CSN on the additional CIS or and 9th stage-
effective date of this AD CSN, whichever through-12th stage occurs first HPC disks using:
(i) 19,000 or more.............. 500 CIS or 20,000 Paragraph (j) of CSN.
this AD. (ii) 17,000 or more, but fewer 1,000 CIS or
Paragraph (j) of than 19,000.
19,500 CSN.
this AD. (iii) 9,000 or more, but fewer 18,000 CSN........ Paragraph (j) of than 17,000.
this AD. (iv) Fewer than 9,000 that are If the parts have Paragraph (j) of accessible.
been inspected this AD. and are acceptable, parts may be reinstalled. Inspect again using the criteria in (iii) of this table.
As part of relaxing the requirements, we also clarified that paragraphs (f)(3) and (j) pertain to 7th stage HPC disks and 9th stage- through-12th stage HPC disks coated with PWA 110-21.
Finally, since AD 2006-17-07 was issued, we received multiple instances of operators requesting clarification of compliance paragraph (e) in AD 2006-17-07. Based on the frequency of requests, we decided to clarify the paragraph. AD 2006-17-07 paragraph (e) originally read as follows:
``(e) You must accomplish the actions required by this AD within the compliance times specified, unless the actions have already been done. Any engine with an HPC front hub that has been inspected using AD 2002-23-14, AD 2003-12-07, or AD 2003-16-05, is considered in compliance with this AD.''
We rewrote paragraph (e) to now read as follows:
``(e) You must accomplish the actions required by this AD within the compliance times specified, unless the actions have already been done. Any engine with an HPC front hub that has been inspected for fretting wear using AD 2002-23-14, AD 2003-12-07, or AD 2003-16-05, counts as an inspection toward compliance with this AD.''
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or develop on other Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, - 9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 turbofan engines of the same type design. We are issuing this AD to prevent a rupture of an HPC front hub or an HPC disk that could result in an uncontained engine failure and damage to the airplane. This AD requires either replacing HPC front hubs and HPC disks that have operated at any time with PWA 110-21 coating and that operated in certain engine models, or, visually inspecting and FMPI for cracking of those parts and re-plating them if they pass inspection.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are unnecessary, and that good cause exists for making this amendment effective in less than 30 days.
Docket Number Change
We are transferring the docket for this AD to the Docket Management System as part of our on-going docket management consolidation efforts. The new Docket No. is FAA-2006-25809. The old Docket No. became the Directorate Identifier, which is 2001-NE-30-AD. This AD might get logged into the DMS docket, ahead of the previously collected documents from the old docket file, as we are in the process of sending those items to the DMS.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism implications under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive Order 12866;
[[Page 61397]]
(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.
We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
0 Under 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
0 1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0 2. The FAA amends Sec. 39.13 by removing Amendment 39-14728 (71 FR 51459, August 30, 2006), and by adding a new airworthiness directive, Amendment 39-14791, to read as follows:
2006-17-07R1 Pratt & Whitney: Amendment 39-14791. Docket No. FAA- 2006-25809; Directorate Identifier 2001-NE-30-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective November 2, 2006.
Affected ADs
(b) This AD revises AD 2006-17-07.
Applicability
(c) This AD applies to the following Pratt & Whitney (PW) JT8D- 1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 turbofan engines, with 8th stage high pressure compressor (HPC) front hubs:
Table 1.--AD Applicability
If the HPC front hub is coated And if the stage 8-9 with:
spacer is coated with: And the HPC front hub: Then this AD is:
(1) PWA 110-21 at any time......... Any................... Operated in a JT8D-15, - Applicable. See 15A, -17, -17A, -17R, or - paragraph (f) and 17AR engine.
Table 2 of this AD. (2) PWA 110-21 at any time......... Any................... Operated in a JT8D-209, - Applicable. See 217, -217A, -217C, or -219 paragraph (h) and engine.
Table 4 of this AD. (3) Nickel-Cadmium................. PWA 110-21 at any time Operated in a JT8D-209, - Applicable. See 217, -217A, -217C, or -219 paragraph (i) and engine.
Table 5 of this AD. (4) Nickel-Cadmium................. PWA 110-21 at any time Operated in a JT8D-1, -1A, - Not applicable. 1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, or -17AR engine. (5) PWA 110-21 at any time......... Any................... Operated in a JT8D-1, -1A, - Not applicable. 1B, -7, -7A, -7B, -9, -9A, or -11, but never operated in a JT8D-15, -15A, -17, - 17A, -17R, -17AR, -209, - 217, -217A, -217C, or -219 engine. (6) Nickel-Cadmium................. Any type but PWA 110- Any........................ Not applicable. 21.
These engines are installed on, but not limited to, Boeing DC-9, MD-80 series, 727 series, and 737 series airplanes.
Unsafe Condition
(d) This AD results from inadvertent reference errors and omissions found in AD 2006-17-07, which could affect ability to comply with that AD. We are issuing this AD to prevent a rupture of an HPC front hub or an HPC disk that could result in an uncontained engine failure and damage to the airplane.
Compliance
(e) You must accomplish the actions required by this AD within the compliance times specified, unless the actions have already been done. Any engine with an HPC front hub that has been inspected for fretting wear using AD 2002-23-14, AD 2003-12-07, or AD 2003-16-05, counts as an inspection toward compliance with this AD.
JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, - 17R, and -17AR Turbofan Engines--Inspect or Replace HPC Front Hubs, HPC Disks, and Stage 8-9 Spacers
(f) For applicable JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR turbofan engines specified in Table 1 of this AD, do the following:
(1) Using the inspection schedule in Table 2 of this AD, strip the protective coating, visually inspect for fretting wear, fluorescent magnetic particle inspect (FMPI) for cracks, reidentify, replate HPC front hubs and stage 8-9 spacers, and replace if necessary.
(2) Use paragraphs 1. through 3.B.(7)(b) under ``For Rear Compressor Front Hubs that Have Operated With PWA 110-21 coating AT ANY TIME During Their Service Life in JT8D-15, -15A, -17, -17A, - 17R, -17AR Engine Models.'' of PW Alert Service Bulletin (ASB) JT8D A6468, dated December 23, 2004.
Table 2.--HPC Front Hub Inspection Schedule
Inspect before Also inspect 7th HPC front hub cycles-since-new additional cycles- stage HPC disks (CSN) on the effective date of in-service (CIS) and 9th stage- this AD
or CSN, whichever through-12th stage occurs first HPC disks using:
(i) 19,000 or more.............. 500 CIS or 20,000 Paragraph (f)(3) CSN.
of this AD. (ii) 15,500 or more, but fewer 1,000 CIS or
Paragraph (f)(3) than 19,000.
19,500 CSN.
of this AD. (iii) 5,000 or more, but fewer 16,500 CSN........ Paragraph (f)(3) than 15,500.
of this AD.
[[Page 61398]]
(iv) Fewer than 5,000 that are If the parts have Paragraph (f)(3) accessible.
been inspected of this AD. and are acceptable, parts may be reinstalled. Inspect again using the criteria in (iii) of this Table.
(3) When the HPC front hub is inspected, visually inspect for fretting wear and FMPI for cracks on 7th stage HPC disks and 9th stage-through-12th stage HPC disks coated with PWA 110-21. Inspection information can be found in the applicable sections of JT8D Engine Manual Part Number (P/N) 481672, listed in the following Table 3:
Table 3.--Seventh Stage HPC Disks and 9th Stage-Through-12th Stage HPC Disks Inspection Information
Chapter/
Fretting Stage
section Visual inspection inspection
FMPI
7..............................
72-36-41 Inspection-01.... Inspection-04.... Inspection-03. 9..............................
72-36-43 Inspection-01.... Inspection-04.... Inspection-03. 10.............................
72-36-44 Inspection-01.... Inspection-04.... Inspection-03. 11.............................
72-36-45 Inspection-01.... Inspection-04.... Inspection-03. 12.............................
72-36-46 Inspection-01.... Inspection-04.... Inspection-03.
JT8D-15, -15A, -17, -17A, -17R, and -17AR Turbofan Engines--Cycle Adjustment for HPC Front Hubs That Entered Service With Nickel-Cadmium Plating and PWA 110-21 Coating
(g) For JT8D-15, -15A, -17, -17A, -17R, and -17AR turbofan engines with front hubs that entered service with Nickel-Cadmium plating, but have also operated during the life of the hub with PWA 110-21 coating:
(1) You are allowed to make a cycle adjustment if the hub was never operated with a PWA 110-21-coated stage 8-9 spacer.
(2) Use the information under ``Compliance'' of PW ASB JT8D A6468, dated December 23, 2004, to determine the adjustment.
JT8D-209, -217, -217A, -217C, and -219 Turbofan Engines--Inspect or Replace HPC Front Hubs and Stage 8-9 Spacers
(h) For applicable JT8D-209, -217, -217A, -217C, and -219 turbofan engines specified in Table 1, Row (2) of this AD, do the following:
(1) Using the inspection schedule in Table 4 of this AD, strip the protective coating, visually inspect for fretting wear, FMPI for cracking, reidentify, replate HPC front hubs and the stage 8-9 spacers, and replace if necessary.
(2) Use paragraphs 1. through 1.A. and paragraphs 2. through 2.C.(2)(g)2 of Accomplishment Instructions of PW ASB JT8D A6430, Revision 2, dated December 23, 2004.
Table 4.--HPC Front Hub Inspection Schedule--Hubs Coated With PWA 110-21
Also inspect 7th Inspect before stage HPC disks
HPC front hub CSN on the additional CIS or and 9th stage-
effective date of this AD CSN, whichever through-12th stage occurs first HPC disks using:
(i) 19,000 or more.............. 500 CIS or 20,000 Paragraph (j) of CSN.
this AD. (ii) 15,500 or more, but fewer 1,000 CIS or
Paragraph (j) of than 19,000.
19,500 CSN.
this AD. (iii) 5,000 or more, but fewer 16,500 CSN........ Paragraph (j) of than 15,500.
this AD. (iv) Fewer than 5,000 that are If the parts have Paragraph (j) of accessible..
been inspected this AD. and are acceptable, parts may be reinstalled. Inspect again using the criteria in (iii) of this Table.
(i) For applicable JT8D-209, -217, -217A, -217C, and -219 turbofan engines specified in Table 1, Row (3) of this AD, do the following:
(1) Using the inspection schedule in Table 5 of this AD, strip the protective coating, visually inspect for fretting wear, FMPI for cracking, reidentify, replate HPC front hubs and the stage 8-9 spacers, and replace if necessary.
(2) Use paragraphs 1., 1.C, and 4. through 4.B.(2)(g)2 of Accomplishment Instructions of PW ASB JT8D A6430, Revision 2, dated December 23, 2004, for all applicable hubs with any type of coating.
Table 5.--HPC Front Hub Inspection Schedule--Hubs Coated With Nickel- Cadmium
Also inspect 7th Inspect before stage HPC disks
HPC front hub CSN on the additional CIS or and 9th stage-
effective date of this AD CSN, whichever through-12th stage occurs first HPC disks using:
(i) 19,000 or more.............. 500 CIS or 20,000 Paragraph (j) of CSN.
this AD. (ii) 17,000 or more, but fewer 1,000 CIS or
Paragraph (j) of than 19,000.
19,500 CSN.
this AD. (iii) 9,000 or more, but fewer 18,000 CSN........ Paragraph (j) of than 17,000.
this AD. (iv) Fewer than 9,000 that are If the parts have Paragraph (j) of accessible.
been inspected this AD. and are acceptable, parts may be reinstalled. Inspect again using the criteria in (iii) of this Table.
[[Page 61399]]
(j) When the HPC front hub is inspected, visually inspect for fretting wear and FMPI for cracks on 7th stage HPC disks and 9th stage-through-12th stage HPC disks coated with PWA 110-21. Inspection information can be found in the applicable sections of JT8D-200 Engine Manual P/N 773128, listed in Table 3 of this AD.
JT8D-209, -217, -217A, -217C, and -219 Turbofan Engines--Cycle Adjustment for HPC Front Hubs That Entered Service With Nickel-Cadmium Plating and PWA 110-21 Coating
(k) For JT8D-209, -217, -217A, -217C, and -219 turbofan engines with HPC front hubs that entered service with Nickel-Cadmium plating, but have also operated during the life of the hub with PWA 110-21 coating:
(1) You are allowed to make a cycle adjustment.
(2) Use the information under ``CONDITION A'' of PW ASB JT8D A6430, Revision 2, dated December 23, 2004, to determine the adjustment.
Replacement of HPC Front Hubs and Stage 8-9 Spacers That Have Operated With PWA 110-21 Coating, As Optional Action--All Engines
(l) For all applicable engines, as an optional action for the visual inspections in this AD, replace HPC front hubs and stage 8-9 spacers that have operated with PWA 110-21 coating in the interface between the hub and the stage 8-9 spacer and HPC disks currently coated with PWA 110-21, as follows:
(1) Install a Nickel-Cadmium plated HPC front hub that has never operated with PWA 110-21 coating in the interface between the HPC front hub and the stage 8-9 spacer.
(2) Install a Nickel-Cadmium plated or Electroless Nickel-plated stage 8-9 spacer.
(3) Install HPC disks that have never operated with PWA 110-21 coating.
Prohibition Against Recoating the HPC Front Hub, Stage 7 HPC Disk, and Stage 8-9 Spacer With PWA 110-21--All Engines
(m) Do not recoat the HPC front hub with PWA 110-21 (Repair-23 of Chapter/Section 72-36-42 of JT8D-200 Engine Manual, P/N 773128, and Repair-27 and Repair-28 of Chapter/Section 72-36-42 of JT8D Engine Manual, P/N 481672).
(n) Do not recoat the 7th stage disk with PWA 110-21 (Repair-15 of Chapter/Section 72-36-41 of JT8D-200 Engine Manual, P/N 773128, and Repair-15 of Chapter/Section 72-36-41 of JT8D Engine Manual, P/N 481672).
(o) Do not recoat the stage 8-9 spacer with PWA 110-21 (Repair- 03, Task 72-36-12-30-003-002, of Chapter/Section 72-36-12 of JT8D- 200 Engine Manual, P/N 773128, and Repair-01, Task 72-36-12-30-001- 002, of Chapter/Section 72-36-12 of JT8D Engine Manual, P/N 481672).
Prohibition Against Reinstalling HPC Front Hubs and Stage 8-9 Spacers Coated With PWA 110-21
(p) After the effective date of this AD, do not reinstall HPC front hubs and stage 8-9 spacers coated with PWA 110-21.
Definition
(q) For the purpose of this AD, ``accessible'' is defined as when the HPC front hub is removed from the engine and the hub is debladed.
Alternative Methods of Compliance
(r) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19.
Related Information
(s) None.
Material Incorporated by Reference
(t) You must use the service information specified in Table 6 of this AD to perform the actions required by this AD. The Director of the Federal Register previously approved the incorporation by reference of these alert service bulletins in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as of October 4, 2006 (71 FR 51459, August 30, 2006). Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108, telephone (860) 565-7700; fax (860) 565-1605 for a copy of this service information. You may review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Table 6.--Incorporation by Reference
Pratt & Whitney Alert Service Bulletin No.
Page
Revision
Date
JT8D A6430, Total Pages: 35.... ALL.................... 2...................... December 23, 2004. JT8D A6468, Total Pages: 20.... ALL.................... Original............... December 23, 2004.
Issued in Burlington, Massachusetts, on October 11, 2006. Thomas A. Boudreau, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6-17327 Filed 10-17-06; 8:45 am]
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